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US20110127701A1 - Dynamic control of lance utilizing co-flow fluidic techniques - Google Patents

Dynamic control of lance utilizing co-flow fluidic techniques Download PDF

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Publication number
US20110127701A1
US20110127701A1 US12/628,124 US62812409A US2011127701A1 US 20110127701 A1 US20110127701 A1 US 20110127701A1 US 62812409 A US62812409 A US 62812409A US 2011127701 A1 US2011127701 A1 US 2011127701A1
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US
United States
Prior art keywords
jet
gas
lance
conduit
outlet
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US12/628,124
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English (en)
Inventor
Michael G.K. Grant
Fabien Januard
Youssef Joumani
Jacky Laurent
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
LAir Liquide SA pour lEtude et lExploitation des Procedes Georges Claude
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
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Priority to US12/628,124 priority Critical patent/US20110127701A1/en
Assigned to L'AIR LIQUIDE, SOCIETE ANONYME POUR L'ETUDE ET L'EXPLOITATION DES PROCEDES GEORGES CLAUDE reassignment L'AIR LIQUIDE, SOCIETE ANONYME POUR L'ETUDE ET L'EXPLOITATION DES PROCEDES GEORGES CLAUDE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GRANT, MICHAEL G.K., JANUARD, FABIEN, JOUMANI, YOUSSEF, LAURENT, JACKY
Priority to TW099141190A priority patent/TW201144734A/zh
Priority to PCT/US2010/058368 priority patent/WO2011066550A1/fr
Publication of US20110127701A1 publication Critical patent/US20110127701A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D3/00—Charging; Discharging; Manipulation of charge
    • F27D3/16—Introducing a fluid jet or current into the charge
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21C—PROCESSING OF PIG-IRON, e.g. REFINING, MANUFACTURE OF WROUGHT-IRON OR STEEL; TREATMENT IN MOLTEN STATE OF FERROUS ALLOYS
    • C21C5/00—Manufacture of carbon-steel, e.g. plain mild steel, medium carbon steel or cast steel or stainless steel
    • C21C5/28—Manufacture of steel in the converter
    • C21C5/42—Constructional features of converters
    • C21C5/46—Details or accessories
    • C21C5/4606—Lances or injectors
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21C—PROCESSING OF PIG-IRON, e.g. REFINING, MANUFACTURE OF WROUGHT-IRON OR STEEL; TREATMENT IN MOLTEN STATE OF FERROUS ALLOYS
    • C21C5/00—Manufacture of carbon-steel, e.g. plain mild steel, medium carbon steel or cast steel or stainless steel
    • C21C5/52—Manufacture of steel in electric furnaces
    • C21C5/5211—Manufacture of steel in electric furnaces in an alternating current [AC] electric arc furnace
    • C21C5/5217—Manufacture of steel in electric furnaces in an alternating current [AC] electric arc furnace equipped with burners or devices for injecting gas, i.e. oxygen, or pulverulent materials into the furnace
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21C—PROCESSING OF PIG-IRON, e.g. REFINING, MANUFACTURE OF WROUGHT-IRON OR STEEL; TREATMENT IN MOLTEN STATE OF FERROUS ALLOYS
    • C21C7/00—Treating molten ferrous alloys, e.g. steel, not covered by groups C21C1/00 - C21C5/00
    • C21C7/04—Removing impurities by adding a treating agent
    • C21C7/072—Treatment with gases
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21C—PROCESSING OF PIG-IRON, e.g. REFINING, MANUFACTURE OF WROUGHT-IRON OR STEEL; TREATMENT IN MOLTEN STATE OF FERROUS ALLOYS
    • C21C7/00—Treating molten ferrous alloys, e.g. steel, not covered by groups C21C1/00 - C21C5/00
    • C21C7/10—Handling in a vacuum
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27B—FURNACES, KILNS, OVENS OR RETORTS IN GENERAL; OPEN SINTERING OR LIKE APPARATUS
    • F27B3/00—Hearth-type furnaces, e.g. of reverberatory type; Electric arc furnaces ; Tank furnaces
    • F27B3/10—Details, accessories or equipment, e.g. dust-collectors, specially adapted for hearth-type furnaces
    • F27B3/22—Arrangements of air or gas supply devices
    • F27B3/225—Oxygen blowing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/20—Recycling

Definitions

  • One application is a non-ferrous metallurgical furnace. It is known to provide a layer of liquefied inert gas such as Argon over a bath of molten for the purpose of avoiding the pickup of oxygen from the atmosphere above the bath.
  • the Argon is typically introduced above the bath as a stream of liquefied gas.
  • the liquefied gas pools above the bath and vaporizes to produce an expanding gas which drives out any oxygen above the surface of the bath.
  • the Argon is introduced above the bath using a fixed lance. While the prior art methods have provided a fairly satisfactory solution, such methods utilizing a fixed lance do not achieve maintenance of a uniform layer of liquefied gas above a large area of the bath while at the same time avoiding overconsumption of the Argon.
  • Some non-ferrous processes utilize oxygen for refining.
  • An example is the refining of copper. Copper is inert relative to other metals so oxygen and/or air can be used to oxidize dissolved elements. Oxygen and/air can also be used to impart the correct amount of dissolved oxygen for certain applications such as copper rod.
  • Non ferrous baths often have a large surface area that would normally be poorly mixed. A moveable lance would provide more uniform application of oxygen and/or air.
  • EAFs electric arc furnaces
  • the materials to be melted are introduced at the top of the furnace.
  • the EAF may be equipped with burners delivering a power of several megawatts.
  • This combustion of fuel (mainly natural gas but sometimes fuel-oil) with oxygen brings heat to initiate melting of the scrap.
  • the scrap in front of the burners is heated first.
  • the burner must have a high momentum flames for at least a few reasons.
  • high momentum flames are needed to avoid the deviation of the flame towards the walls or even towards the burner panel.
  • a cutting operation in the electric arc furnace occurs during the scrap melting phase when the scrap is hot but not molten.
  • heat transfer between oxy-fuel burner flame and the scrap is no longer efficient so final melting in the “cold spots” is performed using oxygen and the mechanism of heating is chemical energy provided by the oxygen reacting with the scrap.
  • Cutting is used normally by operating oxy-fuel burners with excess oxygen or by using the door lance through the slag door.
  • a refining operation in an electric arc furnace deals with the removal of primarily carbon, but also phosphorus, sulfur, aluminum, silicon and manganese from the steel.
  • refining operations are carried out once the steel scrap is completely melted and involves oxidation of the above mentioned impurities through injection of a supersonic oxygen jet into the molten bath. Removal of carbon impurities is referred to as the decarburization process, a process which occurs in the steel bath and in a slag-gas-steel emulsion after the burner operation is stopped.
  • the refining step in the EAF is also called the “hard lance mode”. It includes reactions between C (coal particles and dissolved carbon in the melt), CO, CO 2 and O 2 which provided by the supersonic lance.
  • the oxidation of carbon generates CO bubbles that can flush from the bath dissolved gases such as hydrogen and nitrogen, which are also recognized as a concern.
  • the injected oxygen also lowers the bath carbon content to the desired level for tapping. Because most of the other non-carbon impurities during refining have a higher affinity for oxygen than carbon, oxygen preferentially reacts with these elements to form oxides which can be removed in the resultant slag.
  • an EAF tool such as a burner or lance can be described by the distance of the tool from the nominal steel bath surface.
  • the lance is typically located a distance of 0.5 to 2 meters above the steel bath.
  • a foaming slag (CO bubbles) created by the carbon-oxygen reaction during carbon injection, floats on the steel bath.
  • a burner and a supersonic lance are combined into a single multifunction tool.
  • the implementation of such a tool depends mainly on the furnace type, the composition and quality of the raw materials.
  • the angle of injection (with respect to horizontal) of the supersonic O 2 jet is often around 40-45° from the horizontal. However, this value can be as high as 50° and it will depend upon the construction of the furnace.
  • fixing this angle has the effect of fixing the area of the steel bath surface that is targeted by the supersonic jet. If only a portion of the bath can be stirred by impingement of the jet upon the targeted portion, the overall refining reaction is limited by the relatively slow diffusion of oxygen through the non-targeted/unstirred portions of the bath. Acceleration of the overall refining process thus often requires the use of multiple tools for separately targeting multiple portions of the bath.
  • a fixed angle of attack limits the ability of the lance to generate a thick foamy slag on the bath surface over more than just the targeted area. This is important because quick generation of thick, foamy slag across much of the bath surface decreases the tap-to-tap time and increases furnace productivity. Speedier generation of the thick, foamy slag often requires the use of several lances each one of which targets a specific portion of the bath.
  • a lance is provided that comprises a main body having a primary conduit and a secondary conduit formed therein and upstream and downstream ends.
  • a jet of a gas is injected from the outlet of the primary conduit and into the reaction space.
  • a vacuum is applied to the secondary conduit to create a counterflow of a gas into the secondary conduit outlet from the reaction space interior and to cause deviation of the jet towards the counterflow.
  • Each of the primary and secondary conduits extends between a respective inlet and a respective outlet, the outlets being disposed at the downstream end.
  • An outlet of the secondary conduit is disposed at a location adjacent the primary conduit outlet.
  • a lance comprising a main body, a source of a first gas, and a source of vacuum.
  • the main body has a primary conduit and a secondary conduit formed therein and upstream and downstream ends. Each of the primary and secondary conduits extends between a respective inlet and a respective outlet, the outlets being disposed at the downstream end. An outlet of the secondary conduit is disposed at a location adjacent the primary conduit outlet.
  • the source of the first gas is at a pressure higher than ambient and it fluidly communicates with the primary conduit.
  • the source of vacuum is in selective fluid communication with the secondary conduit.
  • a lance comprising a main body having a primary conduit and a secondary conduit formed therein and upstream and downstream ends.
  • a jet of a first gas is injected from the outlet of the primary conduit and into the reaction space.
  • a second gas is injected from the outlet of the secondary conduit to create a co-flow of the second gas adjacent to a peripheral region of the jet such that the jet is deviated towards the co-flow of second gas.
  • the first and second gases are the same or different.
  • Each of the primary and secondary conduits extends between a respective inlet and a respective outlet, the outlets being disposed at the downstream end.
  • An outlet of the secondary conduit is disposed at a location adjacent the primary conduit outlet.
  • the system comprises: a lance comprising a main body, a source of a first gas, and a source of a second gas.
  • the main body has a primary conduit and a secondary conduit formed therein and upstream and downstream ends. Each of the primary and secondary conduits extends between a respective inlet and a respective outlet, the outlets being disposed at the downstream end. An outlet of the secondary conduit is disposed at a location adjacent the primary conduit outlet.
  • the source of the first gas is at a higher than ambient pressure and it fluidly communicates with the primary conduit.
  • the source of the second gas is at a higher than ambient pressure and is in selective fluid communication with the secondary conduit.
  • the first and second gases are the same or different.
  • the source of second gas is at a pressure higher than that of the source of the first gas.
  • the lance for injecting a jet of a first gas into an interior of a reaction space.
  • the lance comprises: a main body having upstream and downstream ends and primary and secondary conduits formed therein; and a collar comprising a wall extending around the primary and secondary conduit outlets from the main body downstream end.
  • Each of the primary and secondary conduits extends between an associated inlet and an associated outlet, each of the primary and secondary conduit outlets being disposed at the downstream end.
  • a terminal portion of the primary conduit at the downstream end extends along an axis.
  • the primary conduit inlet is adapted to be placed in fluid communication with a source of a first gas.
  • the secondary conduit inlet is adapted to be placed in fluid communication with a source of vacuum or a source of a second gas.
  • An inner surface of the collar wall diverges away from the primary conduit axis to define a vectoring space adapted to allow expansion of a jet of the first gas exiting the primary conduit outlet.
  • the source of the first gas is the same as or different from the source of the second gas.
  • the secondary conduit outlet is disposed at a location adjacent the primary conduit outlet sufficient to fluidically deviate a jet of the first gas exiting the primary conduit outlet towards the collar inner wall surface adjacent the secondary conduit outlet when the secondary conduit inlet is placed in fluid communication with either the vacuum source or the source of the second gas.
  • Any of the disclosed methods, systems, or lance may include one or more of the following aspects:
  • FIG. 1A is a schematic cross-sectional view of a counterflow embodiment of the invention.
  • FIG. 1B is a schematic cross-sectional view of a co-flow embodiment of the invention.
  • FIG. 1C is a schematic cross-section of a collar having an inner wall surface that diverges concavely away from the axis of the jet.
  • FIG. 1D is a schematic cross-section of a collar having an inner wall surface that diverges in a straight line away from the axis of the jet.
  • FIG. 2A is a isometric view of a lance whose jet may be deviated between opposite sides of an ellipsoid collar wall.
  • FIG. 2B is a top view of the lance of FIG. 2A .
  • FIG. 2C is an expanded section of the top view of FIG. 2A .
  • FIG. 3 is a cross-sectional view of the lance of FIGS. 1 , 2 A, and 2 B taken along line A-A.
  • FIG. 4 is a cross-sectional view of the lance of FIGS. 1 , 2 A, 2 B, and 3 taken along line B-B.
  • FIG. 5A is a top view of a lance whose jet may be deviated between different lobes of a tri-lobed collar wall.
  • FIG. 5B is an expanded section of the top view of FIG. 5A .
  • FIG. 6 is a isometric view of the lance of FIG. 5 .
  • FIG. 7 is a top view of a lance whose jet may be deviated between different corners of a triangular collar wall.
  • FIG. 8 is a isometric view of the lance of FIG. 7 .
  • FIG. 9 is a top view of the lance of FIG. 7 with the top collar 39 B removed.
  • FIG. 10 is a isometric view of a lance whose jet may be deviated between different corners of a square collar wherein each of one pair of opposed corners is associated with a collar wall groove.
  • FIG. 11 is the isometric view of FIG. 10 with portions broken away.
  • FIG. 12A is an exploded, isometric view of the lance of FIGS. 10 and 11 wherein all corners are associated with collar wall grooves.
  • FIG. 12B is an expanded section of the exploded, isometric view of FIG. 12A .
  • FIG. 13A is a top view of the lance of FIGS. 10 , 11 , 12 A, and 12 B.
  • FIG. 13B is an expanded section of the top view of FIG. 13A .
  • FIG. 15 is a cross-sectional view of the lance of FIGS. 10 , 11 , 12 A- 12 B, 13 A- 13 B, and 14 A- 14 D taken along line A-A.
  • FIG. 16 is a isometric view of a lance whose jet may be deviated between different quarters of a circular collar wall that are separated by dividers.
  • FIG. 17 is a top view of the lance of FIG. 15 .
  • FIG. 18 is a cross-sectional view of the lance of FIGS. 15 and 16 taken along line A-A.
  • FIG. 19 is a schematic top view of an application of the lance in which the jet is horizontally swept.
  • FIG. 20 is a schematic side view of an application of the lance in which the jet is vertically swept.
  • FIG. 21 is an isometric view of a lance with an extended collar with one segment removed.
  • FIG. 22 is an isometric view of the lance of FIG. 21 with two segments removed.
  • FIG. 23 is a top view of the lance of FIGS. 21-22 .
  • FIG. 24 is a cross-sectional view of the lance of FIGS. 21-23 taken along line A-A.
  • the invention is directed to a lance, lancing systems, and methods for injecting a gaseous substance into a reaction space wherein fluidic techniques are utilized to deviate a jet of gaseous substance in a desired direction.
  • a lance used according to the method includes a main body having upstream and downstream ends and a primary conduit formed therein and at least one secondary conduit formed therein.
  • Each of the primary and secondary conduits extend between an associated inlet and an associated outlet each of which is disposed at the downstream end of the main body.
  • the primary conduit inlet is adapted to be placed in fluid communication with a source of a first gas.
  • the secondary conduit inlet is adapted to be placed in fluid communication with either a source of vacuum or a source of a second gas.
  • the lance may optionally include a collar.
  • the collar includes a wall extending around the primary and secondary conduit outlets from the main body downstream end. An inner surface of the wall defines a vectoring space adapted to allow a jet of the first gas exiting the primary conduit outlet to flow therethrough.
  • the source of the first gas may be the same as or different from the source of the second gas.
  • the secondary conduit outlet is disposed at a location adjacent the primary conduit outlet sufficient to fluidically deviate a jet of the first gas exiting the primary conduit outlet towards the collar inner wall surface adjacent the secondary conduit outlet when the secondary conduit inlet is placed in fluid communication with either the vacuum source or the source of the second gas.
  • a counter-flow embodiment of a method according to the invention includes the following steps.
  • a jet of the first gas is injected from the outlet of the primary conduit and into the reaction space.
  • a vacuum is applied to the secondary conduit to create a counterflow of a gas into the secondary conduit outlet from the reaction space interior and the jet is deviated towards the counterflow.
  • a co-flow embodiment of a method according to the invention includes the following steps.
  • a jet of the first gas is injected from the outlet of the primary conduit and into the reaction space.
  • a second gas is injected from the outlet of the secondary conduit to create a co-flow of the second gas parallel to an axis of the jet and adjacent a peripheral region of the jet.
  • the jet is deviated towards the co-flow of second gas.
  • the co-flow itself is overexpanded.
  • the first and second gases may be the same or different.
  • the axis along which the secondary conduit is oriented may be parallel or at an angle to an axis along which the primary conduit is oriented. In the latter case, the two axes diverge as they proceed from an upstream direction to a downstream direction. In this manner, the secondary conduit is not oriented towards the primary conduit so as to cause direct impingement of the co-flow upon the jet and momentum transfer.
  • the jet angle may be controlled by using a secondary flow (co-flow or counterflow) that is adjacent to the jet whereby the ratio of the static pressure of the secondary flow to that of the jet at the outlets is less than 1.
  • a secondary flow co-flow or counterflow
  • the jet is deviated or “bent” towards the secondary flow.
  • the static pressure of the secondary flow is sub atmospheric.
  • the ratio may be achieved in two different ways: with a secondary flow that flows in a direction opposite that of the jet (counterflow) or with a secondary flow that flows in the same direction as that of the jet (co-flow). Regardless of whether the counterflow or co-flow alternatives are used, use of this technique allows continuous deviating or bending (i.e., vectoring) of the jet from zero to a maximum deviation angle.
  • FIG. 1A A counterflow embodiment of this vectoring is illustrated in FIG. 1A .
  • a main flow MF of a first gas flows through a primary conduit that extends through a main body of a lance and whose terminal portion includes nozzle N 1 .
  • the main flow MF exits the nozzle N 1 along an axis X and emerges as a jet J.
  • a secondary conduit also extends through the lance in between the nozzle N 1 and the collar C 1 . If a vacuum is applied to produce a first counterflow CF 1 in the secondary conduit, the jet J is vectored/deviated by an angle ⁇ 1 away from the axis X and towards one side of the collar C 1 .
  • the lance includes another secondary conduit also extending between the nozzle N 1 and the collar C 1 on a side of the jet J opposite that of the first counterflow F 1 .
  • the vacuum is instead applied to produce a second counterflow CF 2 in this other secondary conduit, the jet J is vectored/deviated by an angle ⁇ 2 away from the axis X and towards the opposite side of the collar C 1 .
  • the vacuum is alternatingly applied to opposite areas adjacent the jet J to produce alternation between counterflow F 1 and counterflow F 2
  • the total angle by which the jet J is deviated by the alternating counterflows F 1 , F 2 is the sum of the individual angles ⁇ 1 + ⁇ 2 and the jet J is swept across a target area generally described by a straight line.
  • the vacuum may be supplied by an external vacuum pump fluidly communicating with the secondary conduit through which the counterflow is desired.
  • the vacuum may be supplied with an external ejector pump using compressed gas.
  • compressed gas such as air
  • An opening in the nozzle is disposed in the diverging portion of the ejector pump adjacent the nozzle's neck. This opening fluidly communicates with the secondary conduit in the lance.
  • the vacuum may instead be supplied by another lance in which case the primary conduit in the other lance is a converging-diverging nozzle. In this manner, a lance utilizing counterflow is supplied with vacuum from another lance associated with the reaction space and which is operated without counterflow.
  • This other lance may be identical to the lance of FIG. 1A and operable according to the invention or it may be different.
  • FIG. 1B A co-flow embodiment of this vectoring is illustrated in FIG. 1B .
  • a main flow MF of the first gas flows through a primary conduit that extends through a main body of a lance and whose terminal portion includes nozzle N 2 .
  • the main flow MF exits the nozzle N 2 along an axis X and emerges as a jet J.
  • the lance also includes two secondary conduits each one of which extends through a different portion of the lance between the nozzle N 2 and the collar C 2 .
  • a co-flow CF 3 of a second gas (which may the same as or different from the first gas) emerges from one of the secondary conduits.
  • the static pressure of the co-flow CF 3 and of the jet J is a function of the upstream pressure of the supply of the gases for the co-flow CF 3 and the jet J and also of the geometrical configuration of the nozzle N 2 and collar C 2 .
  • the pressures of the gases upstream of the nozzle N 2 for each of the jet J and co-flow CF 3 and the configuration of the nozzle N 2 are selected such that the static pressure of the co-flow CF 3 adjacent the jet J is lower than of the main jet J.
  • an operator simply may increase the upstream pressure of the second gas for co-flow CF 3 in an empirical manner until a sufficient deviation by an angle ⁇ 3 away from the axis X and towards the co-flow CF 3 is observed. If deviation of the jet J in the opposite direction is desired, co-flow CF 3 is discontinued and a co-flow CF 4 of the second gas is initiated through the other of the secondary conduits on an opposite side of the jet J.
  • the pressures of the gases upstream of the nozzle N 2 for each of the jet J and co-flow CF 4 and the configuration of the nozzle N 2 are selected such that the static pressure of the co-flow CF 4 adjacent the main jet J is lower than of the jet J.
  • an operator may simply increase the upstream pressure of the gaseous substance for co-flow CF 4 in an empirical manner until a sufficient deviation by an angle ⁇ 4 is observed.
  • the total angle by which the jet J is deviated by the alternating co-flows F 3 , F 4 is the sum of the individual angles ⁇ 3 + ⁇ 4 and the jet J is swept across a target area generally described by a straight line.
  • each single deviation angle may reach as high as 45°.
  • angles beyond 45° may cause the jet to reach too close to the enclosed structure may cause significant damage thereto.
  • FIGS. 1A and 1B illustrate specific configurations, such configurations are not essential to the invention. Rather, the lance need only have a primary conduit through which the first gas flows and a secondary conduit through which flows either the counterflow or the co-flow. While a collar is not essential to the invention, use of a collar brings some benefits. In the counterflow embodiment, the collar serves as a surface against which the jet may attach by the Coanda effect. Thus, the deviation of the jet is rendered more accurate and repeatable. Also, the collar serves to lower the degree of vacuum required in comparison to when no collar is used.
  • the collar may be of rotating type.
  • the collar may have an outer plate having one or more openings for the counterflow or co-flow that is rotatable with respect to the rest of the lance. In this manner, rotation of the outer plate may allow a counterflow or co-flow adjacent one region of the jet while disallowing such a counterflow or co-flow at another region of the jet. Further rotation of the outer plate may disallow the first counterflow or co-flow while allowing the second counterflow or co-flow.
  • the collar is a structure that extends from a main body of the lance adjacent the primary and secondary conduit outlets to a downstream extremity of the lance.
  • the collar includes a wall that extends around the outlets of the primary conduit (from which the jet emanates) and the outlet(s) of the secondary conduit(s).
  • the inner surface of the wall defines a vectoring space and provides a surface upon which the jet may attach given sufficient deviation by the fluidic means of the counterflow or co-flow. While the wall may partially surround the outlets, it is believed that better performance is realized when the wall completely surrounds the outlets.
  • the inner wall surface may be configured in a variety of shapes.
  • a cross-sectional shape of the inner wall surface may be a circle, ellipse, square, triangle, tri-lobed, four-lobed, five-lobed, six-lobed, a pentagon, or a hexagon.
  • Regular polygons with more than six sides are also included within the scope of the invention but are somewhat less preferred because of the relatively greater difficulty in attaching the jet to a particular side.
  • the inner wall surface may also include dividers that extend inwardly towards the jet. These dividers serve the purpose of partially dividing the space enclosed by the inner wall surface into a plurality of vectoring sub-spaces.
  • Each of the plurality of vectoring sub-spaces is associated with a respective secondary conduit outlet allowing a respective counterflows or co-flow therethrough.
  • the dividers should not be overly long such that their innermost edges interfere with the jet. Instead of dividers, the plurality of vectoring sub-spaces may be separated by a plurality of gas curtains.
  • the vectoring space may still be divided into a plurality of vectoring sub-spaces. This may be accomplished by selecting a collar wall inner surface configuration whose cross-section along the axis of the primary conduit is different from that of the primary conduit outlet. For example, if the primary conduit outlet has a circular cross-sectional shape, while the collar wall inner surface could have an ellipsoid, square, triangular, tri-lobed, four-lobed, five-lobed, six-lobed, pentagonal, or hexagonal cross-sectional shape.
  • the primary conduit outlet and collar wall inner surface configurations and relative sizes are selected such that the peripheral regions of the jet touch the collar inner wall surface at a plurality of tangency points.
  • a properly sized primary conduit outlet and triangular collar wall inner surface will yield a centrally disposed circular area accommodating the jet as well as three vectoring sub-spaces.
  • each of the vectoring sub-spaces is defined by a portion of one of the corners of the triangle and an arc that extends along a partial circumference of the jet.
  • the primary conduit outlet could have a square cross-sectional shape and the collar inner wall surface could have a circular cross-section.
  • a properly sized primary conduit and a properly sized collar inner wall will yield a centrally disposed square area accommodating the jet as well as four circular segments.
  • Each of the circular segments would have an outer boundary consisting of an arc and an inner boundary consisting of a chord that extends along one of the sides of the jet.
  • the collar inner wall surface can extend parallel to the axis of the primary conduit.
  • the collar wall inner surface can and preferably does diverge outwardly away from the primary conduit axis.
  • the divergence may take any of several configurations, two of which will now be described
  • a collar C 3 has a wall portion with a height H 3 that extends downstream from an outlet of the primary conduit N 3 from which the jet J 3 originates.
  • the height of the inner collar wall is typically between about one to five times the width or diameter D 3 of the nozzle N 3 or jet J 3 .
  • a gap G 3 between the nozzle N 3 and the collar C 3 at the outlet of the nozzle N 3 (representing the width or diameter of the counterflow or co-flow) is typically anywhere between 0.01 to 2.0 times the width/diameter D 3 of the nozzle N 3 or jet J 3 .
  • the inner wall surface IW 3 smoothly diverges concavely away from an axis X 3 of the nozzle N 3 (which also corresponds to an axis of the jet J 3 when it is not deviated according to the invention).
  • a collar C 4 has a wall portion with a height H 4 that extends downstream from an outlet of the primary conduit N 3 from which the jet J 4 originates.
  • the height of the inner collar wall is typically between about one to five times the width or diameter D 4 of the nozzle N 4 or jet J 4 .
  • a gap G 4 between the nozzle N 4 and the collar C 4 at the outlet of the nozzle N 4 (representing the width or diameter of the counterflow or co-flow) is typically anywhere between 0.01 to 2.0 times the width/diameter D 4 of nozzle N 4 or jet J 4 .
  • the inner wall surface IW 4 diverges in a straight line away from an axis X 4 of the nozzle N 4 (which also corresponds to an axis of the jet J 4 when it is not deviated according to the invention).
  • the invention may be practiced with the collars of FIGS. 1C and 1D in either the co-flow or the counterflow embodiments.
  • the collar of course provides a maximum limit to which the jet may be deviated. Under conditions where the jet has not been deviated sufficiently to attach it to the collar, increasing the static pressure ratio between the jet and the co-flow or counterflow will further deviate the jet until it attaches. Once it attaches, further increases in the static pressure ratio between the jet and the co-flow or counterflow will have no further effect upon the jet deviation angle so long as the nozzle, Mach number and flow rates remain constant.
  • the maximum deviation angle can be varied by modifying the nozzle design, and when a collar is utilized, the collar design.
  • the maximum deviation angle can also be varied by changing the Mach number or by changing the flow rate of the primary jet (by increasing its upstream pressure), or in the case of the counterflow embodiment the level of vacuum may be increased.
  • a counterflow may be applied to the desired region of deviation while no flow or a positive flow (at relatively low pressures/flow rates) of the first gas may be allowed at other regions.
  • a co-flow may be applied to the desired region of deviation while other openings are kept open. Similarly other openings could be blocked for preventing any flow therethrough.
  • the invention also allows dynamic control of the lance.
  • varying the degree of vacuum applied to create the counterflow can result in deviation of the jet to any angle in between zero and the maximum angle without requiring reconfiguration of the lance.
  • alternation between two different counterflows or co-flows on different sides of the jet will result in alternating vectoring of the jet in different directions.
  • the jet may be swept across a desired target area instead of being directed towards only one spot. Because this is done fluidically, there is no need for moving parts susceptible to corrosion from the high temperature of and/or gases from the furnace. Rather, alternation between the two counterflows or co-flows may be achieved by remotely alternating application of a vacuum or high pressure second gas to different conduits that are in fluid communication with the secondary conduit outlets.
  • the vectoring of the jet may follow a pattern in which case the alternation between the various counterflows or co-flows may be controlled with a programmable logic controller.
  • the jet is typically vectored in anywhere between 1 to 6 different directions.
  • the jet is typically deviated from the axis extending from the primary conduit outlet towards 1 to 6 different directions.
  • a greater number of vectoring directions is possible with the caveat that relatively less accurate deviations of the jet are believed to occur with such high numbers of vectoring directions.
  • a circular jet may be vectored in any number of directions depending upon the placement and number of secondary conduit outlets.
  • the jet may be swept in any number of different ways: horizontally, vertically, diagonally, etc.
  • the jet may be swept in a repeated pattern or be swept in an irregular manner. Such repeated or irregular sweeping may be controlled with the use of a programmable logic controller written with an algorithm adapted to control application of the counterflow or co-flow to the appropriate secondary conduit for accomplishing the desired sweep conditions.
  • the jet may be of any gas (the first gas) desired for injection into a reaction space including, but are not limited to, oxygen, oxygen-enriched air, natural gas and inert gases such as nitrogen or argon. In the case of oxygen, it typically has a purity of from 90-100%.
  • the second gas may be the same as the first gas or different. Typically, the second gas is the same as the first gas, but at a higher pressure.
  • the co-flow can be at ambient temperature (also called “cold”) or preheated. Preheating decreases the mixing rate between the jet and the co-flow.
  • the velocity of the jet may be supersonic or subsonic, typically in the range of from about 0.3 Mach to about 5.0 Mach.
  • the flow rate of the jet is typically anywhere between about 200 Nm 3 /h to about 4000 Nm 3 /h while the co-flow is typically about 50 Nm3/h to about 1200 Nm 3 /h.
  • the width or diameter of the co-flow is typically 0.01 to about 2.0 times the width or diameter of jet.
  • the flow rate can be much higher (for example 10,000 Nm 3 /h).
  • they can be ideally expanded or under-expanded.
  • Types of reaction spaces receiving the injected first gas include, but are not limited to, EAFs, BOFs, QBOP, AODs, VODs, and non-ferrous foundries.
  • the reactant in the reaction space is a liquid or a solid and includes, but is not limited to, steel, metal parts, and non-ferrous metals.
  • the primary conduit outlet may have a square, rectangular, elliptical, circular, triangular, pentagonal, or hexagonal cross-section.
  • the primary conduit and primary conduit outlet preferably have a circular or square cross-section.
  • the lance also includes at least one secondary conduit (typically one to six but sometimes more. While the cross-section of the secondary conduit outlet may have any configuration, in the counterflow mode the secondary conduit outlet is preferably kidney bean shaped when the primary conduit outlet is circular. In such a case, the concave portion of the kidney bean shape extends along a peripheral region of the primary conduit outlet. This arrangement is believed to achieve the lowest pressure drop across the vacuum conduit in comparison to secondary conduit outlets of different configurations.
  • the lance can have water cooling jackets around it in order to protect them from relatively high temperatures that may be encountered in a reaction space comprising a furnace.
  • one lance embodiment includes a collar 9 secured to a main body 7 with fasteners inserted through bores 11 .
  • a converging-diverging primary conduit is formed in a main body 7 .
  • the primary conduit extends between an inlet 1 and outlet 12 and includes a straight section 2 , a converging section 4 which narrows to a neck 6 , and a diverging section 8 which extends along an axis.
  • Two secondary conduits are formed in the collar 9 .
  • the first secondary conduit extends between an inlet 3 A and an outlet 14 A, while the second secondary conduit extends between an inlet 3 B and an outlet 14 B. While FIGS.
  • the collar 9 includes a wall that circumferentially extends from and around the primary conduit outlet 12 and secondary conduit outlets 14 A, 14 B and extends in a downstream direction to terminate in a beveled surface B.
  • the inner surface of the collar wall has an ellipsoid cross-sectional shape. The middle portion of the inner wall surface extends in a direction parallel to an axis of the primary conduit.
  • Adjacent each secondary conduit outlet 14 A, 14 B are corresponding inner wall surface end portions 5 A, 5 B.
  • the end portions 5 A, 5 B diverge outwardly at an oblique angle to the primary conduit axis.
  • a jet gas (which for clarity's sake will be termed the first gas) exits the primary conduit outlet 12 along the axis of the primary conduit.
  • the inner wall surface defines a vectoring space into which the jet can expand.
  • the collar 9 and main body 7 are typically machined separately and are fastened together as described above. However, they may be formed in a single integral piece and later machined to form all of the necessary structures.
  • a vacuum is supplied to the inlet 3 A of one of the secondary conduits.
  • inlet 3 B can be open or closed or a coflow of the second gas can also be supplied through it.
  • a flow of gas (which for clarity's sake will be termed the second gas but which may have the same or different composition as the first gas) is allowed through a secondary conduit and exits outlet 14 A.
  • the pressures of the sources of first and second gases upstream of the primary and secondary conduits are selected such that the static pressure of the co-flow adjacent the jet is lower than of the jet. This creates a pressure differential between the co-flow and the jet which deviates the jet towards the end portion 5 A. Given a sufficiently great pressure differential, the jet “attaches” to the end portion 5 A of the inner wall surface to produce a stable deviated jet.
  • the jet is deviated towards the end portion 5 B and attach given a sufficiently high pressure differential.
  • a sufficiently higher velocity of the co-flowing second gas adjacent the jet will create the pressure differential necessary for deviation of the jet.
  • an operator may adjust the pressure of the second gas upstream of the secondary conduit in an empirical manner in order to achieve a desired velocity for the co-flow and thus a desired pressure differential.
  • another lance embodiment includes a collar 29 secured to a main body 7 with fasteners inserted through bores 11 .
  • a converging-diverging primary conduit is formed in the main body 7 and extends along an axis.
  • the primary conduit extends between an inlet and outlet 12 .
  • Three secondary conduits are formed in the collar 29 .
  • the first secondary conduit extends between an inlet 3 A and an outlet 24 A, while the second and third secondary conduits correspondingly extend between inlets 3 B, 3 C and outlets 24 B, 24 C.
  • the collar 29 includes a wall that circumferentially extends from and around the primary conduit outlet 12 and secondary conduit outlets 24 A, 24 B, 24 C and extends in a downstream direction to terminate in a beveled surface B 2 .
  • the inner surface of the collar wall has a three-lobed cross-sectional shape.
  • Each of the secondary conduit outlets 24 A, 24 B, 24 C is disposed adjacent to and immediately upstream of a respective collar wall inner surface lobe portion 25 A, 25 B, 25 C.
  • the collar wall inner surface also includes inwardly extending partial dividers 25 G, 25 E, 25 F that separate adjacently disposed lobe portions 25 A and 25 B, 25 B and 25 C, and 25 C and 25 A, respectively.
  • the collar wall inner surface extends in a direction parallel to the axis of the primary conduit at each of the dividers 25 G, 25 E, 25 F but diverges outwardly away from the primary conduit outlet 12 at the lobe portions 25 A, 25 B, 25 C.
  • the first gas exits the primary conduit outlet 12 as a jet along the axis of the primary conduit.
  • the inner collar wall surface defines a vectoring space into which the jet can expand.
  • the collar 29 and main body 7 are typically machined separately and are fastened together as described above. However, they may be formed in a single integral piece and later machined to form all of the necessary structures.
  • a vacuum is supplied to the inlet 3 A of one of the three secondary conduits. This creates a region of sub atmospheric pressure adjacent a peripheral region of the jet in the vectoring space downstream of outlet 24 A. Due to the pressure differential between the region of sub atmospheric pressure and the jet, the jet is deviated at an angle to the axis of the primary conduit towards lobe portion 25 A. Given a sufficient degree of applied vacuum, the jet will “attach” to the lobe portion 25 A to produce a stable deviated jet.
  • a flow of the second gas is allowed through a secondary conduit and exits outlet 24 A.
  • the pressures of the sources of first and second gases upstream of the primary and secondary conduits are selected such that the static pressure of the co-flow adjacent the jet is lower than of the jet. This creates a pressure differential between the co-flow and the jet which deviates the jet towards the lobe portion 25 A. Given a sufficiently great pressure differential, the jet “attaches” to the lobe portion 25 A to produce a stable deviated jet.
  • the jet is deviated towards a respective lobe portion 25 B, 25 C and attaches given a sufficiently high pressure differential.
  • a sufficiently higher velocity of the co-flowing second gas adjacent the jet will create the pressure differential necessary for deviation of the jet.
  • an operator may adjust the pressure of the second gas upstream of the secondary conduit in an empirical manner in order to achieve a desired velocity for the co-flow and thus a desired pressure differential.
  • another lance embodiment includes an intermediate collar 39 A secured to a main body 7 with fasteners inserted through bores 11 and a top collar 39 B secured to the intermediate collar 39 A with fasteners inserted through bores S 3 .
  • a converging-diverging primary conduit is formed in the main body 7 and extends along an axis.
  • the primary conduit extends between an inlet and outlet 12 .
  • Three secondary conduits are formed in the intermediate collar 39 A.
  • the first secondary conduit extends between an inlet 3 A and an outlet 34 A, while the second and third secondary conduits correspondingly extend between inlets 3 B, 3 C and outlets 34 B, 34 C.
  • the top collar 39 A includes a wall that circumferentially extends from and around the primary conduit outlet 12 and secondary conduit outlets 34 A, 34 B, 34 C and extends in a downstream direction to terminate in a beveled surface B 3 .
  • the inner surface of the top collar wall has a triangular cross-sectional shape with rounded corners.
  • Each of the secondary conduit outlets 34 A, 34 B, 34 C is disposed adjacent to and immediately upstream of a respective corner 35 A, 35 B, 35 C of the inner wall surface of the top collar 39 B. Except for the corners 35 A, 35 B, 35 C, the inner wall surface of the top collar 39 B extends in a direction parallel to the axis of the primary conduit.
  • the inner wall surface of the top collar 39 B diverges outwardly away from the primary conduit outlet 12 .
  • the first gas exits the primary conduit outlet 12 as a jet along the axis of the primary conduit.
  • the inner wall surface of the top collar 39 B defines a vectoring space into which the jet can expand.
  • the intermediate collar 39 A, top collar 39 B, and main body 7 are typically machined separately and are fastened together as described above. However, they may be formed in a single integral piece and later machined to form all of the necessary structures.
  • a vacuum is supplied to the inlet 3 A of one of the three secondary conduits. This creates a region of sub atmospheric pressure adjacent a peripheral region of the jet in the vectoring space downstream of outlet 34 A. Due to the pressure differential between the region of sub atmospheric pressure and the jet, the jet is deviated at an angle to the axis of the primary conduit towards corner 35 A. Given a sufficient degree of applied vacuum, the jet will “attach” to the corner 35 A to produce a stable deviated jet. Similarly, application of vacuum to an inlet 3 B, 3 C of one of the other secondary conduits will deviate the jet towards corner 35 B, 35 C, respectively and attach given a sufficient degree of vacuum. For a given flow rate of the first gas through a given lance, the degree of vacuum may be adjusted in an empirical manner to determine and optimal level.
  • a flow of the second gas is allowed through a secondary conduit and exits outlet 34 A.
  • the pressures of the sources of first and second gases upstream of the primary and secondary conduits are selected such that the static pressure of the co-flow adjacent the jet is lower than of the jet. This creates a pressure differential between the co-flow and the jet which deviates the jet towards the lobe portion 35 A. Given a sufficiently great pressure differential, the jet “attaches” to corner 35 A to produce a stable deviated jet.
  • the jet is deviated towards a respective corner 35 B, 35 C and attaches given a sufficiently high pressure differential.
  • a sufficiently higher velocity of the co-flowing second gas adjacent the jet will create the pressure differential necessary for deviation of the jet.
  • an operator may adjust the pressure of the second gas upstream of the secondary conduit in an empirical manner in order to achieve a desired velocity for the co-flow and thus a desired pressure differential.
  • another lance embodiment includes an intermediate collar 49 A secured to a main body 7 with fasteners inserted through bores 11 and a top collar 49 B secured to the intermediate collar 49 A with fasteners inserted through bores S 4 .
  • a converging-diverging primary conduit is formed in the main body 7 and extends along an axis between an inlet and outlet 12 . It includes a straight section 2 , a converging section which narrows to a neck 6 and a diverging section.
  • Four secondary conduits are formed in the intermediate collar 49 A.
  • the first secondary conduit extends between an inlet 3 A and an outlet 44 A, while the second, third, and fourth secondary conduits correspondingly extend between inlets 3 B, 3 C, 3 D and outlets 44 B, 44 C, 44 D, respectively.
  • the top collar 49 A includes a wall that circumferentially extends from and around the primary conduit outlet 12 and secondary conduit outlets 44 A, 44 B, 44 C, 44 D.
  • Each of the secondary conduit outlets 44 A, 44 B, 44 C, 44 D is disposed adjacent to and upstream of a respective corner 45 A, 45 B, 45 C, 45 D of the inner wall surface of the top collar 39 B.
  • the inner surface of the top collar wall has a generally frustopyramidal (frustum of a pyramid) shape with four corners 45 A, 45 B, 45 C, 45 D and grooves G formed in two corners 45 A, 45 C.
  • the first gas exits the primary conduit outlet 12 as a jet along the axis of the primary conduit and the grooved, frustopyramidal top collar inner wall surface defines a vectoring space into which the jet can expand.
  • Each groove G represents the portion of the associated corner 45 A, 45 C that is machined away in order to project the cross-sectional shape of the secondary conduit outlets 44 A, 44 C in the downstream direction parallel to the primary conduit axis.
  • the frustopyramidal aspect of the top collar inner wall surface includes a small base adjacent the primary and secondary conduit outlets 12 , 44 A, 44 B, 44 C, 44 D and a large base at the downstream extremity of top collar 49 B.
  • the narrow base has a pair of opposite corners 45 B, 45 D.
  • curved surfaces 145 A, 145 C In between curved surface 145 A and corner 45 B is a jutting portion 145 A′ while jutting portion 145 A′′ is in between curved surface 145 A and corner 45 D.
  • Jutting portions 145 C′, 145 C′′ are in between curved surface 145 C & corner 45 B and curved surface 145 C and corner 45 D, respectively.
  • the cross-section of the frustopyramidal aspect of the inner surface of the top collar wall increases in the downstream direction.
  • corners 45 C, 45 A emerge in cross-sectional view in FIG. 14C and become even more prominent in FIGS. 14D , 14 E.
  • the grooves G extend from secondary conduit outlets 44 A, 44 C in a direction parallel to the axis of the primary conduit, the curved surfaces 145 A, 145 C remain static relative to the axis of the primary conduit and are eventually swallowed up by corners 45 A, 45 C.
  • intermediate collar 39 A, top collar 39 B, and main body 7 are typically machined separately and are fastened together as described above. However, they may be formed in a single integral piece and later machined to form all of the necessary structures.
  • a vacuum is supplied to the inlet 3 A of one of the four secondary conduits.
  • the jet will “attach” to the curved surface 145 A and corner 45 A to produce a stable deviated jet.
  • application of vacuum to an inlet 3 C of another of the other secondary conduits will deviate the jet towards curved surface 145 C and corner 45 C and attach given a sufficient degree of vacuum.
  • the vacuum is supplied to the inlet 3 B of one of the two remaining secondary conduits, a region of sub atmospheric pressure is created that is bounded by the frustopyramidal inner surface of the top collar wall at corner 45 B, jutting portions 145 A′, 145 C′, and a peripheral region of the jet.
  • the curved surfaces 145 A, 145 C are also believed to more easily create the regions of sub atmospheric pressure adjacent the peripheral region of the jet in comparison to the top collar wall inner surface adjacent corners 45 B, 45 D. While the lance of FIGS. 10 , 11 , 12 A- 12 B, 13 A- 13 B, 14 A- 14 D, and 15 illustrates grooves G formed only in corners 45 A, 45 C, it is understood that similar grooves may be formed in the top collar inner wall surface in corners 45 B, 45 D. Conversely, each of the corners 45 A, 45 B, 45 C, 45 D may be grooveless.
  • a flow of the second gas is allowed through a secondary conduit and exits outlet 44 A in between curved surface 145 A and corner 45 A, jutting portions 145 A′, 145 A′′ and a peripheral region of the jet.
  • the pressures of the sources of first and second gases upstream of the primary and secondary conduits are selected such that the static pressure of the co-flow adjacent the jet is lower than of the jet. This creates a pressure differential between the co-flow and the jet which deviates the jet towards the curved surface 145 A and corner 45 A.
  • the jet “attaches” to the curved surface 145 A and corner 45 A to produce a stable deviated jet.
  • the jet is deviated towards a respective curved surface 145 C and corner 45 C and attaches given a sufficiently high pressure differential.
  • the flow of the second gas may exit outlet 44 B in between corner 45 B, jutting portions 145 A′, 145 C′ and a peripheral region of the jet and be deviated towards corner 45 B and attach given a sufficiently great enough pressure differential.
  • another lance embodiment includes an intermediate collar 59 A secured to a main body 57 with fasteners inserted through bores 11 and a top collar 59 B secured to the intermediate collar 59 A with fasteners inserted through bores S 5 .
  • a primary conduit is formed in the main body 7 and extends along an axis. The primary conduit extends between an inlet 1 and outlet 52 includes an upstream straight section 52 , a diverging section 54 , and a downstream straight section 56 .
  • Four secondary conduits are formed in the intermediate collar 59 A.
  • the first secondary conduit extends between an inlet 53 A and an outlet 54 A, while the second, third, and fourth secondary conduits correspondingly extend between inlets 53 B, 53 C, 53 D and outlets 54 B, 54 C, 54 D.
  • the top collar 59 A includes a wall that circumferentially extends from and around the primary conduit outlet 12 and secondary conduit outlets 54 A, 54 B, 54 C, 54 D and extends in a downstream direction to terminate in a beveled surface B 5 .
  • the inner surface of the top collar wall is a frustoconical surface (surface of a frustum of a cone) and includes four sections 55 A, 55 B, 55 C, 55 D. The inner surface of the top collar wall diverges in the direction of the jet along the axis of the primary conduit.
  • the top collar includes four axially distributed slots each one of which extends through the side wall of the top collar and the top collar inner wall surface.
  • the slots are sized to accommodate four dividers W 1 , W 2 , W 3 , and W 4 which partially extend out of the slots at the side wall of the top collar and partially extend inwards from the top collar inner wall surface.
  • the dividers W 1 , W 2 , W 3 , W 4 also extend in a direction parallel to the divergence of the collar wall inner surface from immediately downstream of the primary and secondary conduit outlets 52 , 54 A, 54 B, 54 C, 54 D and up to the beveled surface B 5 .
  • the first gas exits the primary conduit outlet 12 as a jet along the axis of the primary conduit.
  • the inner wall surface of the top collar 59 B defines a vectoring space into which the jet can expand.
  • Each of the secondary conduits 54 A, 54 B, 54 C, 54 D is disposed adjacent to and immediately upstream of a respective quarter portion 55 A, 55 B, 55 C, 55 D of the inner wall surface of the top collar 39 B.
  • Each combination of two of the four dividers W 1 , W 2 , W 3 , W 4 and the quarter portion 55 A, 55 B, 55 C, 55 D that they bound defines a vectoring sub-space into which the jet may be deviated according to the mechanism of the invention.
  • one of the four vectoring sub-spaces is defined by the combination of divider W 1 , quarter portion 55 B, and divider W 2 .
  • the intermediate collar 59 A, top collar 59 B, main body 7 , and dividers W 1 , W 2 , W 3 , W 4 are typically machined separately and are fastened together as described above. However, they may be formed in a single integral piece and later machined to form all of the necessary structures. Additionally, the dividers W 1 , W 2 , W 3 , W 4 need not project outwardly from a side of the top collar 59 B.
  • a vacuum is supplied to the inlet 53 A of one of the four secondary conduits. This creates a region of sub atmospheric pressure adjacent a peripheral region of the jet in the vectoring space downstream of outlet 54 A. Due to the pressure differential between the region of sub atmospheric pressure and the jet, the jet is deviated at an angle to the axis of the primary conduit and into the vectoring sub-space defined by divider W 4 , quarter portion 55 A, and divider W 1 . Given a sufficient degree of applied vacuum, the jet will “attach” to the quarter portion 55 A to produce a stable deviated jet.
  • a flow of the second gas is allowed through a secondary conduit and exits outlet 54 A.
  • the pressures of the sources of first and second gases upstream of the primary and secondary conduits are selected such that the static pressure of the co-flow adjacent the jet is lower than that of the jet. This creates a pressure differential between the co-flow and the jet which deviates the jet into the vectoring sub-space defined by divider W 4 , quarter portion 55 A, and divider W 1 . Given a sufficiently great pressure differential, the jet will attach to quarter portion 55 A to produce a stable deviated jet.
  • the jet is deviated into a respective vectoring sub-spaces defined by the various combinations of dividers W 1 , W 2 , W 3 , W 4 and quarter portions 55 B, 55 C, 55 D.
  • dividers W 1 , W 2 , W 3 , W 4 and quarter portions 55 B, 55 C, 55 D are dividers W 1 , W 2 , W 3 , W 4 and quarter portions 55 B, 55 C, 55 D.
  • an operator may adjust the pressure of the second gas upstream of the secondary conduit in an empirical manner in order to achieve a desired velocity for the co-flow and thus a desired pressure differential.
  • FIGS. 2A-18 illustrate that the inlet of the secondary conduit is positioned on a side of the collar, it can be positioned anywhere on the collar including a position near the inlet of the primary conduit on or adjacent the main body.
  • 1-10 lances according to the invention can be used in order to increase foamy slag generation.
  • the invention may be applied to metallurgical vessels other than EAFs in which case it may be used to inject inert gases, in particular, Argon or Nitrogen. Many of such vessels exhibit poor mixing behavior that may be alleviated with supersonic injection of an inert gas jet via the invention for the purpose of stirring a relatively large area of the bath contained therein.
  • the lance When the lance is used to inject oxygen into an EAF, it may serve several different functions depending upon which stage the metallurgical process is in: 1) melting, 2) beginning of the refining, 3) first half of refining, and 4) last half of refining.
  • the dynamic lance is used as a classical supersonic lance without deviation of the jet.
  • the oxygen flowing in the lance is used as complementary oxygen for combustion or for post-combustion.
  • the lance is used in supersonic mode for scrap cutting and for initiating the refining.
  • the lance may be swept in a pattern at a relatively low frequency (typically one degree per second) in order to get an efficient cut of the scrap.
  • the lance could also be used as a classical lance as well.
  • the lance could be horizontally and/or vertically swept in a regular pattern for increasing bath area coverage for greater refining efficiency.
  • the jet could be horizontally and/or vertically swept at a relatively higher frequency in order to promote better stirring and increase the foamy slag quality.
  • the EAF 100 includes electrodes 110 which create hotspots 120 .
  • a plurality of supersonic lances 130 inject oxygen across a target area described by an arc sweeping across an angle ⁇ .
  • a relative large area of the bath 140 in the EAF 100 can have oxygen injected therein.
  • the lances 130 may be swept in a horizontal pattern.
  • the lances 130 may be swept in a vertical pattern. As described above, combinations of vertical and horizontal sweeping are also possible.
  • the invention yields several advantages. When applied to metallurgical furnaces. It helps to reduce the tap-to-tap time through an increase in the bath area coverage. It also achieves better stirring of the bath. It further allows achievement of an optimal angle of attack. It allows dynamic control of the lance without subjecting moving parts to corrosive furnace gases and temperatures.
  • the sweeping motion of the jet also prevents the localized generation of FeO caused by the oxidization of steel. It is well known that FeO is very corrosive to refractories so the sweeping motion will reduce the localized concentration in the slag. Thus, it reduces O2 waste and improves metal yield.
  • Lance design #1 was based upon the lance of FIGS. 16-18 .
  • Lance design #2 was based upon the lance of FIGS. 16-18 but instead of a converging nozzle for the primary conduit, a converging-diverging nozzle was used.
  • Lance design #3 was based upon the lance of FIGS. 2A , 2 B, 2 C, 3 , and 4 .
  • Lance design #4 was based upon the lance of FIGS. 10 , 11 , 12 A- 12 B, 13 A- 13 B, 14 A- 14 D, and 15 where no grooves were formed adjacent to the corners.
  • Lance design #5 was based upon the lance of FIGS.
  • Lance design #6 was based upon a design illustrated in FIGS. 21-24 that includes an intermediate collar between the bottom and top collars that was designed to allow expansion of the jet before fluid contact with a counterflow vacuum stream.
  • Lance design #7 was based upon the lance of FIGS. 7-9 .
  • each lance design achieved a deviation angle of at least 5°.
  • the third and fifth designs were found to have achieved the largest angle. Regardless of the lance design, we observed at most only about a 20% decrease in coherence using Schlerin techniques.

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110127703A1 (en) * 2009-11-30 2011-06-02 Gautam Vivek Dynamic lances utilizing fluidic techniques
US20110127702A1 (en) * 2009-11-30 2011-06-02 Gautam Vivek Dynamic control of lance utilizing counterflow fluidic techniques
US20130323100A1 (en) * 2011-11-24 2013-12-05 Dyson Technology Limited Fan assembly
US20220259686A1 (en) * 2019-07-22 2022-08-18 Jfe Steel Corporation Molten iron dephosphorization method

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10781499B2 (en) * 2018-01-17 2020-09-22 Air Products And Chemicals, Inc. Bottom stirring tuyere and method for a basic oxygen furnace

Citations (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4965813A (en) * 1989-07-25 1990-10-23 Nikko Industry Co., Ltd. Combustion aiding apparatus for steel-making electric-arc-furnace
US5366537A (en) * 1993-01-05 1994-11-22 Steel Technology Corporation Fuel and oxygen addition for metal smelting or refining process
US5814125A (en) * 1997-03-18 1998-09-29 Praxair Technology, Inc. Method for introducing gas into a liquid
US5823762A (en) * 1997-03-18 1998-10-20 Praxair Technology, Inc. Coherent gas jet
US5904895A (en) * 1994-08-29 1999-05-18 American Combustion, Inc. Apparatus for electric steelmaking
US5931985A (en) * 1994-11-18 1999-08-03 Mannesmann Aktiengesellschaft Process and device for blowing oxygen-containing gas with and without solid material on a metal melt in a metallurgical vessel
US5946340A (en) * 1996-03-03 1999-08-31 Georg Fischer Disa Engineering Ag Process for melting of metal materials in a shaft furnace
US6096261A (en) * 1997-11-20 2000-08-01 Praxair Technology, Inc. Coherent jet injector lance
US6125133A (en) * 1997-03-18 2000-09-26 Praxair, Inc. Lance/burner for molten metal furnace
US6139310A (en) * 1999-11-16 2000-10-31 Praxair Technology, Inc. System for producing a single coherent jet
US6176894B1 (en) * 1998-06-17 2001-01-23 Praxair Technology, Inc. Supersonic coherent gas jet for providing gas into a liquid
US6235084B1 (en) * 1995-11-17 2001-05-22 Mannesmann Ag Method for decarburizing steels melts
US6289035B1 (en) * 2000-02-10 2001-09-11 Valery G. Shver Mounting arrangement for auxiliary burner or lance
US6322610B1 (en) * 1998-11-10 2001-11-27 Danieli & C. Officine Meccaniche Spa Integrated device to inject oxygen, technological gases and solid material in powder form and method to use the integrated device for the metallurgical processing of baths of molten metal
US20010052200A1 (en) * 1998-06-08 2001-12-20 Lucio Londero Perfected melting method and device suitable to achieve the method
US6342086B1 (en) * 1999-02-16 2002-01-29 Process Technology International, Inc. Method and apparatus for improved EAF steelmaking
US6372010B1 (en) * 1999-12-10 2002-04-16 Process Technology International, Inc. Method for metal melting, refining and processing
US6400747B1 (en) * 2001-05-18 2002-06-04 Praxair Technology, Inc. Quadrilateral assembly for coherent jet lancing and post combustion in an electric arc furnace
US6432165B1 (en) * 1997-12-04 2002-08-13 Sms Demag Ag Method for injecting gases into a metallurgical tank
US6432163B1 (en) * 2001-06-22 2002-08-13 Praxair Technology, Inc. Metal refining method using differing refining oxygen sequence
US6450799B1 (en) * 2001-12-04 2002-09-17 Praxair Technology, Inc. Coherent jet system using liquid fuel flame shroud
US20030000338A1 (en) * 2000-02-10 2003-01-02 Shver Valery G. Method for particulate introduction for metal furnaces
US6514310B2 (en) * 2000-08-07 2003-02-04 L'air Liquide Societe Anonyme A Directoire Et Conseil De Surveillance Pour L'etude Et L'exploitation Des Procedes Georges Claude Process for injection of a gas with the aid of a nozzle
US20030075843A1 (en) * 2001-08-29 2003-04-24 Empco (Canada) Ltd. Multi-purpose, multi-oxy-fuel, power burner/injector/oxygen lance device
US6614831B2 (en) * 2000-02-10 2003-09-02 Process Technology International, Inc. Mounting arrangement for auxiliary burner or lance
US6669838B1 (en) * 1999-06-21 2003-12-30 Access Business Group International Llc. Apparatus for filtering and sterilizing water utilizing a turbidity and microorganism sensing system
US6749661B2 (en) * 2000-02-10 2004-06-15 Process Technology International, Inc. Method for melting and decarburization of iron carbon melts
US6875398B2 (en) * 2003-01-15 2005-04-05 Praxair Technology, Inc. Coherent jet system with outwardly angled flame envelope ports
US6910431B2 (en) * 2002-12-30 2005-06-28 The Boc Group, Inc. Burner-lance and combustion method for heating surfaces susceptible to oxidation or reduction
US6932854B2 (en) * 2004-01-23 2005-08-23 Praxair Technology, Inc. Method for producing low carbon steel
US20060060028A1 (en) * 2002-06-11 2006-03-23 Cameron Andrew M Refining ferroalloys
US7258831B2 (en) * 2002-07-11 2007-08-21 Danieli & C. Officine Meccaniche S.P.A. Injector-burner for metal melting furnaces
US20080000325A1 (en) * 2006-06-28 2008-01-03 William John Mahoney Oxygen injection method
US7384594B2 (en) * 2002-01-15 2008-06-10 Sms Demag Ag Method for the pyrometallurgical treatment of metals, metal melts and/or slags and injection device
US20080134838A1 (en) * 2005-02-18 2008-06-12 Techint Compagnia Tecnica Internazionale S.P.A Multifunction Injector and Relative Combustion Process for Metallurgical Treatment in an Electric Arc Furnace
US20090311639A1 (en) * 2006-07-06 2009-12-17 L'air Liquide Societe Anonyme Pour L'etude Et L'ex Ploitation Des Procedes Georges Claude Method for Heating a Charge
US20100032020A1 (en) * 2006-07-06 2010-02-11 L'air Liquide Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Method and Apparatus for Injecting a Jet of Fluid with a Variable Direction and/or Opening
US20100068666A1 (en) * 2006-07-06 2010-03-18 L'air Liquide Societe Anonyme Pour L'etude Et L'ex Ploitation Des Procedes Georges Claude Burner the Direction and/or Size of the Flame of Which Can Be Varied, and Method of Implementing It
US20110127703A1 (en) * 2009-11-30 2011-06-02 Gautam Vivek Dynamic lances utilizing fluidic techniques

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB997875A (en) * 1960-10-25 1965-07-07 Beteiligungs & Patentverw Gmbh Process for the production of steels from pig iron
DE3340472A1 (de) * 1983-11-09 1985-05-15 Axel Friedrich 6670 St Ingbert Gonschorek Ld-konverter mit nachverbrennung
JPS6233710A (ja) * 1985-08-07 1987-02-13 Kobe Steel Ltd 転炉における溶鋼昇熱方法
DE10060951A1 (de) * 2000-12-06 2002-06-27 Messer Griesheim Gmbh Verfahren zum Einschmelzen von Metallschrott
EP2080973A1 (fr) * 2008-01-10 2009-07-22 L'AIR LIQUIDE, Société Anonyme pour l'Etude et l'Exploitation des Procédés Georges Claude Fours rotatifs
FR2926296B1 (fr) * 2008-01-10 2011-01-07 Air Liquide Four verrier et procede de fabrication de verre.

Patent Citations (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4965813A (en) * 1989-07-25 1990-10-23 Nikko Industry Co., Ltd. Combustion aiding apparatus for steel-making electric-arc-furnace
US5366537A (en) * 1993-01-05 1994-11-22 Steel Technology Corporation Fuel and oxygen addition for metal smelting or refining process
US5954855A (en) * 1994-08-29 1999-09-21 American Combustion, Inc. Method for electric steelmaking
US5904895A (en) * 1994-08-29 1999-05-18 American Combustion, Inc. Apparatus for electric steelmaking
US5931985A (en) * 1994-11-18 1999-08-03 Mannesmann Aktiengesellschaft Process and device for blowing oxygen-containing gas with and without solid material on a metal melt in a metallurgical vessel
US6235084B1 (en) * 1995-11-17 2001-05-22 Mannesmann Ag Method for decarburizing steels melts
US5946340A (en) * 1996-03-03 1999-08-31 Georg Fischer Disa Engineering Ag Process for melting of metal materials in a shaft furnace
US5823762A (en) * 1997-03-18 1998-10-20 Praxair Technology, Inc. Coherent gas jet
US6125133A (en) * 1997-03-18 2000-09-26 Praxair, Inc. Lance/burner for molten metal furnace
US5814125A (en) * 1997-03-18 1998-09-29 Praxair Technology, Inc. Method for introducing gas into a liquid
US6096261A (en) * 1997-11-20 2000-08-01 Praxair Technology, Inc. Coherent jet injector lance
US6432165B1 (en) * 1997-12-04 2002-08-13 Sms Demag Ag Method for injecting gases into a metallurgical tank
US20010052200A1 (en) * 1998-06-08 2001-12-20 Lucio Londero Perfected melting method and device suitable to achieve the method
US6176894B1 (en) * 1998-06-17 2001-01-23 Praxair Technology, Inc. Supersonic coherent gas jet for providing gas into a liquid
US6383445B1 (en) * 1998-06-17 2002-05-07 Praxair Technology, Inc. Supersonic coherent gas jet for providing gas into a liquid
US6322610B1 (en) * 1998-11-10 2001-11-27 Danieli & C. Officine Meccaniche Spa Integrated device to inject oxygen, technological gases and solid material in powder form and method to use the integrated device for the metallurgical processing of baths of molten metal
US6342086B1 (en) * 1999-02-16 2002-01-29 Process Technology International, Inc. Method and apparatus for improved EAF steelmaking
US6669838B1 (en) * 1999-06-21 2003-12-30 Access Business Group International Llc. Apparatus for filtering and sterilizing water utilizing a turbidity and microorganism sensing system
US6139310A (en) * 1999-11-16 2000-10-31 Praxair Technology, Inc. System for producing a single coherent jet
US6372010B1 (en) * 1999-12-10 2002-04-16 Process Technology International, Inc. Method for metal melting, refining and processing
US6289035B1 (en) * 2000-02-10 2001-09-11 Valery G. Shver Mounting arrangement for auxiliary burner or lance
US20030000338A1 (en) * 2000-02-10 2003-01-02 Shver Valery G. Method for particulate introduction for metal furnaces
US6749661B2 (en) * 2000-02-10 2004-06-15 Process Technology International, Inc. Method for melting and decarburization of iron carbon melts
US6614831B2 (en) * 2000-02-10 2003-09-02 Process Technology International, Inc. Mounting arrangement for auxiliary burner or lance
US6514310B2 (en) * 2000-08-07 2003-02-04 L'air Liquide Societe Anonyme A Directoire Et Conseil De Surveillance Pour L'etude Et L'exploitation Des Procedes Georges Claude Process for injection of a gas with the aid of a nozzle
US6400747B1 (en) * 2001-05-18 2002-06-04 Praxair Technology, Inc. Quadrilateral assembly for coherent jet lancing and post combustion in an electric arc furnace
US6432163B1 (en) * 2001-06-22 2002-08-13 Praxair Technology, Inc. Metal refining method using differing refining oxygen sequence
US20030075843A1 (en) * 2001-08-29 2003-04-24 Empco (Canada) Ltd. Multi-purpose, multi-oxy-fuel, power burner/injector/oxygen lance device
US6450799B1 (en) * 2001-12-04 2002-09-17 Praxair Technology, Inc. Coherent jet system using liquid fuel flame shroud
US7384594B2 (en) * 2002-01-15 2008-06-10 Sms Demag Ag Method for the pyrometallurgical treatment of metals, metal melts and/or slags and injection device
US20060060028A1 (en) * 2002-06-11 2006-03-23 Cameron Andrew M Refining ferroalloys
US7258831B2 (en) * 2002-07-11 2007-08-21 Danieli & C. Officine Meccaniche S.P.A. Injector-burner for metal melting furnaces
US6910431B2 (en) * 2002-12-30 2005-06-28 The Boc Group, Inc. Burner-lance and combustion method for heating surfaces susceptible to oxidation or reduction
US6875398B2 (en) * 2003-01-15 2005-04-05 Praxair Technology, Inc. Coherent jet system with outwardly angled flame envelope ports
US6932854B2 (en) * 2004-01-23 2005-08-23 Praxair Technology, Inc. Method for producing low carbon steel
US20080134838A1 (en) * 2005-02-18 2008-06-12 Techint Compagnia Tecnica Internazionale S.P.A Multifunction Injector and Relative Combustion Process for Metallurgical Treatment in an Electric Arc Furnace
US7611563B2 (en) * 2005-02-18 2009-11-03 Techint Compagnia Tenica Internazionale S.p.A. Multifunction injector and relative combustion process for metallurgical treatment in an electric arc furnace
US20080000325A1 (en) * 2006-06-28 2008-01-03 William John Mahoney Oxygen injection method
US20090311639A1 (en) * 2006-07-06 2009-12-17 L'air Liquide Societe Anonyme Pour L'etude Et L'ex Ploitation Des Procedes Georges Claude Method for Heating a Charge
US20100032020A1 (en) * 2006-07-06 2010-02-11 L'air Liquide Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Method and Apparatus for Injecting a Jet of Fluid with a Variable Direction and/or Opening
US20100068666A1 (en) * 2006-07-06 2010-03-18 L'air Liquide Societe Anonyme Pour L'etude Et L'ex Ploitation Des Procedes Georges Claude Burner the Direction and/or Size of the Flame of Which Can Be Varied, and Method of Implementing It
US20110127703A1 (en) * 2009-11-30 2011-06-02 Gautam Vivek Dynamic lances utilizing fluidic techniques

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110127703A1 (en) * 2009-11-30 2011-06-02 Gautam Vivek Dynamic lances utilizing fluidic techniques
US20110127702A1 (en) * 2009-11-30 2011-06-02 Gautam Vivek Dynamic control of lance utilizing counterflow fluidic techniques
US8323558B2 (en) * 2009-11-30 2012-12-04 L'air Liquide Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Dynamic control of lance utilizing counterflow fluidic techniques
US8377372B2 (en) 2009-11-30 2013-02-19 L'air Liquide Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Dynamic lances utilizing fluidic techniques
US20130323100A1 (en) * 2011-11-24 2013-12-05 Dyson Technology Limited Fan assembly
KR20140087042A (ko) * 2011-11-24 2014-07-08 다이슨 테크놀러지 리미티드 팬 조립체
KR101630719B1 (ko) 2011-11-24 2016-06-15 다이슨 테크놀러지 리미티드 팬 조립체
US10094392B2 (en) * 2011-11-24 2018-10-09 Dyson Technology Limited Fan assembly
US20220259686A1 (en) * 2019-07-22 2022-08-18 Jfe Steel Corporation Molten iron dephosphorization method

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