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EP1998115A1 - Canal de refroidissement destiné à refroidir un composant véhiculant un gaz chaud - Google Patents

Canal de refroidissement destiné à refroidir un composant véhiculant un gaz chaud Download PDF

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Publication number
EP1998115A1
EP1998115A1 EP07010641A EP07010641A EP1998115A1 EP 1998115 A1 EP1998115 A1 EP 1998115A1 EP 07010641 A EP07010641 A EP 07010641A EP 07010641 A EP07010641 A EP 07010641A EP 1998115 A1 EP1998115 A1 EP 1998115A1
Authority
EP
European Patent Office
Prior art keywords
cooling
cooling channel
coolant
wall
channel
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.)
Withdrawn
Application number
EP07010641A
Other languages
German (de)
English (en)
Inventor
Roland Dr. Liebe
Thomas Pechette
Stefan Dahlke
Michael Huth
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP07010641A priority Critical patent/EP1998115A1/fr
Publication of EP1998115A1 publication Critical patent/EP1998115A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a cooling channel according to the preamble of claim 1.
  • the components leading to a hot gas of a gas turbine are preferably cooled by the use of impingement cooling or convection cooling in combination with effusion cooling or film cooling.
  • the combustion chamber in each case has a correspondingly shaped cooling channel.
  • using an open cooling system has disadvantages. For example, the inflow of cooling air previously used for cooling into the combustion chamber reduces the temperature of the hot gas in the combustion chamber.
  • the EP 1 507 116 A1 describes, for example, a cooling channel with an impingement cooling as well as coolant flowing into the combustion chamber.
  • the heat shield arrangement shown surrounds the combustion chamber and comprises a plurality of heat shield elements attached to a support structure, which are arranged side by side, leaving a gap. Between the heat shield elements and the support structure, an interior space is provided into which the coolant for cooling the heat shield elements can flow.
  • the coolant flows through a plurality of, provided in the support structure inlet channels into the interior, wherein the controlled exit of coolant from the interior of a coolant outlet channel is provided, which opens into the gap.
  • the latter relates to a heat shield component for a hot gas wall to be cooled with cooling fluid return and an inlet channel and an outlet channel for the cooling fluid.
  • the inlet channel is directed towards the hot gas wall and widens toward the hot gas wall.
  • the inlet channel, the outlet channel and the closed hot gas wall cause a complete cooling fluid return, so that no losses of cooling fluid are provided by this cooling fluid guide.
  • the EP 1 628 076 A1 describes a cooling channel with concave depressions for improved cooling, wherein the concave depressions are arranged only outside the edge zone on the hot gas wall, while the edge zones remain free or are provided with turbulators.
  • so-called dimples are arranged for particularly effective cooling. This ensures that the cooling fluid is passed in the direction of the edge zones and they are thus increasingly cooled.
  • the arrangement of EP 1 628 076 A1 thus improves the cooling of the edge areas by the installation of turbulators. But even here, a high pressure loss occurs when the coolant enters the cooling channel.
  • a combination of impingement cooling with other turbulence-generating means such as barriers transverse to the flow direction and / or cavities in the cooling channel also have a high pressure loss.
  • the object of the invention is to provide a cooling channel, which is characterized by a particularly low pressure drop and improved cooling of a hot gas-conducting component.
  • the invention is based on the recognition that open cooling, such as film or effusion cooling, is to be avoided since mixing hot gas and coolant brings about significant disadvantages. Furthermore, the invention is based on the knowledge that a good cooling can be achieved with a high cooling gas-side heat transfer coefficient ⁇ while the pressure loss ⁇ p is still low. This means that a favorable quotient ⁇ / ⁇ p can be achieved from heat transfer coefficients and pressure loss.
  • the cooling channel comprises a wall which partially delimits it, a cavity and a cooling wall which is opposite the wall and to be cooled. Through a number of inlet openings in the wall, the coolant flows into the cavity. The coolant can thus at least partially cause an impact cooling of the cooling wall.
  • auxiliary cooling ribs are arranged longitudinally to the flow direction of the coolant in the direction of the outlet opening in the cavity on the cooling wall of the cooling channel.
  • the surface to be cooled substantially and consequently the heat transfer coefficient is increased.
  • the auxiliary cooling ribs can be easily manufactured. The production can be done for example by cold or hot rolling, laser beam cutting, joining thin films or milling. Installation is easy to accomplish in new as well as already existing cooling duct systems.
  • cooling auxiliary ribs differ significantly from previously known cooling fins.
  • cooling fins have a fin height which is substantially greater than the thickness of a boundary layer flow which arises when the flow is purely convective.
  • Cooling riblets By contrast, their height corresponds at most to the thickness of a boundary layer flow with a purely convective flow.
  • the auxiliary cooling ribs have the dimensions in the form of a height h in the direction of the inflow of the coolant, a mean distance s and a comb width t. Furthermore, the inlet openings have a diameter D.
  • all dimensions t, s, h are less than the hydraulic diameter Dp.
  • a particularly good quotient ⁇ / ⁇ p can be achieved from the heat transfer coefficient and pressure loss for the cooling channel according to the invention.
  • the inlet openings may be, for example, round or elliptical, each with a different diameter or a different circumference.
  • the inlet openings are distributed in their arrangement in the wall in the flow direction uniformly or with different density.
  • the inlet openings can also be distributed differently in their arrangement transversely to the flow direction. This can be achieved for example by an offset of inlet openings.
  • a greater density of inlet openings per area may be provided than on the output side.
  • the inlet openings which are also referred to as impact cooling, regularly distributed.
  • the inlet openings are designed as nozzles, so that a particularly efficient impingement cooling of the cooling wall is made possible.
  • the auxiliary cooling ribs are arranged in the cooling channel continuously in the flow direction. As a result, a targeted guidance of the adjusting longitudinal vortex can be achieved and thus improved cooling.
  • auxiliary cooling ribs on the cooling fin comb and / or on the cooling wall bottom and / or on their side walls have vortex-forming elements.
  • the auxiliary cooling ribs may, for example, have a slightly beveled cooling rib comb for this purpose.
  • Other vortex-forming means are also conceivable.
  • such a cooling channel is used on a combustion chamber, in a guide ring or in a turbine blade.
  • the combustion chamber comprises a closed cooling.
  • the at least one outlet opening is adapted to the closed combustion chamber.
  • FIG. 1 On the cooling channel 14 facing side 15 of the cooling wall 12 is a number of parallel cooling auxiliary ribs 3 is arranged extending in the flow direction 2, of which only two are shown.
  • a coolant 1 is injected through schematically represented inlet openings 4 into a cavity 13, ie into the cooling channel 14.
  • the inlet openings 4 are provided in a wall, not shown, which limits the cooling channel 14 on the back.
  • the wall, not shown, is opposite the auxiliary cooling ribs 3 at a distance.
  • the inlet openings 4 are arranged in the wall in a regular pattern.
  • the inlet openings 4 furthermore have a hydraulic diameter D p .
  • the auxiliary cooling ribs 3 have a mean distance s, a comb width t and a height h.
  • the distance s, the comb width t and the height h are substantially smaller than the hydraulic diameter D p , preferably their values are at 5% - 20% of the hydraulic diameter D p .
  • the dimensions of the auxiliary cooling ribs 3 are selected such that preferably one Enlargement of the surface - based on a flat surface - of about 80% results.
  • auxiliary cooling ribs 3 By enlarging the surface to be cooled by means of the auxiliary cooling ribs 3, a significantly improved cooling is achieved. Unexpectedly, however, there is no significant increase in pressure drop.
  • the incoming impact rays are deflected 90 ° and can flow between the cooling auxiliary ribs 3, the riblets. They generate strong spiral longitudinal vortices 9.
  • the longitudinal vortices 9 have a diameter which substantially corresponds to the height of the auxiliary cooling ribs.
  • the injection of the coolant 1 takes place in such a way that pairs of opposing longitudinal vortices 9 are set between two directly adjacent auxiliary cooling ribs 3.
  • the cooling channel 14 has at its ends an outlet (not shown) for the coolant 1. This outlet is designed such that a closed cooling is achieved.
  • the coolant 1 forms, in addition to the longitudinal vortices 9, a comparatively thin boundary layer flow 7 between adjacent auxiliary cooling ribs 3 - on the cooling wall bottom 5 -.
  • the boundary layer flow 7 also applies partially or completely to the side walls of the auxiliary cooling ribs 3.
  • the boundary layer flow 7 has a thickness of 8.
  • the longitudinal vortexes 9 prevent a greater thickness 8 of the boundary layer flow 7, whereby the heat transfer coefficient can be further increased.
  • FIG. 2 shows another example of a cooling channel 14, in which the boundary layer flow 7 has a different thickness 8.
  • the boundary layer is thicker than on the cooling wall bottom 5. This is achieved by specifically arranged and dimensioned inlet openings 4, wherein the coolant 1 impinging on the auxiliary cooling ribs 3 or on their comb 6 at a lower speed (shorter arrows) impinges than on the cooling wall bottom 5 (longer arrows).
  • FIG. 3, 4 and 5 show the execution of a cooling channel 14 according to the invention with auxiliary cooling ribs 3 in a metallic heat shield 18 for the combustion chamber of a gas turbine in a plan, front and side view.
  • the heat shield 18 is attached by a not further shown fastening means to a supporting structure of the combustion chamber.
  • the coolant 1 is injected into the cooling channel 14 through inlet openings 4 arranged in the wall 10 and effects impingement cooling. Subsequently, it flows in the flow direction 2 in the direction of exit (not shown). By the further flow a convection cooling is effected.
  • FIGS. 6 and 7 show a transition part 19 (transition piece) of a pipe combustion chamber. This is arranged between the burners of the combustion chamber and the turbine unit of a stationary gas turbine.
  • the transition part 19 is divided into two areas: in a region R and a region F.
  • cooling auxiliary ribs 3 are longitudinally arranged according to the invention according to the flow direction.
  • the coolant 1 flows through appropriately sized inlet openings 4, whereby an impingement cooling occurs.
  • the coolant 1 subsequently flows through the region F of the transition part 19. This causes convection cooling in the region F.
  • dimples 11 are additionally arranged here.
  • FIGS. 8 to 10 show a liner 20 for a combustion chamber in a top, front and side view. Again, a combination of impingement cooling and subsequent convection cooling is shown.
  • the cooling auxiliary ribs 3 can be arranged partially or else over the entire surface to be cooled longitudinally to the flow direction 2.
  • FIG. 11 shows the use of the cooling channel 14 according to the invention FIG. 1 in a guide ring 21 of a gas turbine, which is provided adjacent to the tips of blades of the turbine.
  • FIG. 12 shows a further advantageous use of the invention within an airfoil of a turbine blade, wherein in detail only the inventively designed leading edge of the airfoil is shown.
  • the present invention thus discloses a cooling channel which is distinguished by a particularly good quotient ⁇ / ⁇ p from the heat transfer coefficient ⁇ to the pressure loss ⁇ p.
  • a film cooling can be avoided hereby and thus also a mixing of hot and cold gases.
  • the cooling channel disclosed here is characterized by a very high heat transfer coefficient for a wide range of coolant Reynolds numbers and low pressure losses.
  • the cooling duct presented here can advantageously also be installed very easily in an existing cooling system. Further advantageous is the simple production of the cooling wall by, for example, cold / hot rolling. It can be used, for example, in heat shield elements or liners, in turbine blades, in transition parts between combustion chamber and turbine (Transistion piece) or other hot gas components.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07010641A 2007-05-29 2007-05-29 Canal de refroidissement destiné à refroidir un composant véhiculant un gaz chaud Withdrawn EP1998115A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07010641A EP1998115A1 (fr) 2007-05-29 2007-05-29 Canal de refroidissement destiné à refroidir un composant véhiculant un gaz chaud

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07010641A EP1998115A1 (fr) 2007-05-29 2007-05-29 Canal de refroidissement destiné à refroidir un composant véhiculant un gaz chaud

Publications (1)

Publication Number Publication Date
EP1998115A1 true EP1998115A1 (fr) 2008-12-03

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP07010641A Withdrawn EP1998115A1 (fr) 2007-05-29 2007-05-29 Canal de refroidissement destiné à refroidir un composant véhiculant un gaz chaud

Country Status (1)

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EP (1) EP1998115A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011048123A3 (fr) * 2009-10-20 2012-12-20 Siemens Aktiengesellschaft Système de combustion multicarburant
CN113483363A (zh) * 2021-08-18 2021-10-08 中国联合重型燃气轮机技术有限公司 燃气轮机及火焰筒

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1530594A (en) * 1974-12-13 1978-11-01 Rolls Royce Perforate laminated material
EP0624757A1 (fr) * 1993-05-10 1994-11-17 General Electric Company Refroidissement récuperatif par impact de jet d'air pour composants de moteur à réaction
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
WO1998013645A1 (fr) * 1996-09-26 1998-04-02 Siemens Aktiengesellschaft Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds
EP1043479A2 (fr) * 1999-04-06 2000-10-11 General Electric Company Paroi de turbine rainurée
EP1306619A2 (fr) * 2001-10-29 2003-05-02 Mitsubishi Heavy Industries, Ltd. Turbine à gaz et chambre de combustion
EP1528322A2 (fr) * 2003-10-23 2005-05-04 United Technologies Corporation Chambre de combustion

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1530594A (en) * 1974-12-13 1978-11-01 Rolls Royce Perforate laminated material
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
EP0624757A1 (fr) * 1993-05-10 1994-11-17 General Electric Company Refroidissement récuperatif par impact de jet d'air pour composants de moteur à réaction
WO1998013645A1 (fr) * 1996-09-26 1998-04-02 Siemens Aktiengesellschaft Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds
EP1043479A2 (fr) * 1999-04-06 2000-10-11 General Electric Company Paroi de turbine rainurée
EP1306619A2 (fr) * 2001-10-29 2003-05-02 Mitsubishi Heavy Industries, Ltd. Turbine à gaz et chambre de combustion
EP1528322A2 (fr) * 2003-10-23 2005-05-04 United Technologies Corporation Chambre de combustion

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011048123A3 (fr) * 2009-10-20 2012-12-20 Siemens Aktiengesellschaft Système de combustion multicarburant
CN102844622A (zh) * 2009-10-20 2012-12-26 西门子公司 一种多燃料燃烧系统
CN102844622B (zh) * 2009-10-20 2015-08-26 西门子公司 一种多燃料燃烧系统
CN113483363A (zh) * 2021-08-18 2021-10-08 中国联合重型燃气轮机技术有限公司 燃气轮机及火焰筒

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