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WO2020050835A1 - Joint d'étanchéité sans contact à ajustement mécanique - Google Patents

Joint d'étanchéité sans contact à ajustement mécanique Download PDF

Info

Publication number
WO2020050835A1
WO2020050835A1 PCT/US2018/049534 US2018049534W WO2020050835A1 WO 2020050835 A1 WO2020050835 A1 WO 2020050835A1 US 2018049534 W US2018049534 W US 2018049534W WO 2020050835 A1 WO2020050835 A1 WO 2020050835A1
Authority
WO
WIPO (PCT)
Prior art keywords
seal
shoe
secondary seal
groove
primary
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.)
Ceased
Application number
PCT/US2018/049534
Other languages
English (en)
Inventor
Jonathon Baker
William HALCHAK
Douglas J. Arrell
Matthew Kelly
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
Siemens Energy Inc
Original Assignee
Siemens AG
Siemens Corp
Siemens Energy Inc
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, Siemens Energy Inc filed Critical Siemens AG
Priority to PCT/US2018/049534 priority Critical patent/WO2020050835A1/fr
Publication of WO2020050835A1 publication Critical patent/WO2020050835A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/441—Free-space packings with floating ring
    • F16J15/442—Free-space packings with floating ring segmented
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/56—Brush seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the present invention relates to seals for sealing a circumferential gap between two machine components that are relatively rotatable with respect to each other, and, more particularly, to a seal having at least one shoe extending along one of the machine components in a position to create a non-contact seal therewith.
  • Labyrinth seals provide adequate sealing, but they are extremely dependent on maintaining radial tolerances at all points of engine operation.
  • the radial clearance must take into account factors such as thermal expansion, shaft motion, tolerance stack-ups, rub tolerance, etc. Minimization of seal clearance is necessary to achieve maximum labyrinth seal effectiveness.
  • Straight-thru labyrinth seals are the most sensitive to clearance changes, with large clearances resulting in a carryover effect.
  • Stepped labyrinth seals are very dependent on axial clearances, as well as radial clearances, which limits the number of teeth possible on each land.
  • Pregrooved labyrinth seals are dependent on both axial and radial clearances, and must have an axial clearance less than twice the radial clearance to provide better leakage performance than stepped seals.
  • Turbomachinery such as gas turbines engines, are becoming larger, more efficient, and more robust. Large blades and vanes are being utilized, especially in the hot section of the engine system. In view of high pressure ratios and high engine firing temperatures implemented in modern engines, certain components, such as airfoils, e.g., stationary vanes and rotating blades, require more efficient sealing capabilities than the ones that exist currently.
  • airfoils e.g., stationary vanes and rotating blades
  • clearance between the rotating and stationary components in turbomachinery are regions of low performance. There are several drivers of aerodynamic loss in the compressor-vane carrier, turbine-shroud cavity configuration, intermediate shaft, and the like, which lowers the turbomachinery’s efficiency.
  • One driver is the flow over the rotating components.
  • the mixing losses that occur downstream of clearance areas are high and contribute to a reduction in stage efficiency and power. Additional mixing losses occur when the flow through the tip cavity combines with the main flow and the two streams have different velocities. Tip leakage is essentially lost opportunity for work extraction. Tip leakage also contributes towards aerodynamic secondary losses.
  • a seal assembly for sealing a circumferential gap between a first machine component and a second machine component which is rotatable relative to the first machine component about a longitudinal axis in the axial direction, comprises: a seal carrier that holds all the components of the seal assembly together along an outer ring; a primary seal comprising: at least one shoe extending along one of the first and second machine components, producing a non-contact seal therewith, the shoe being formed with a slot; at least one spring element adapted to connect to one of the first and second machine components, and being connected to the at least one shoe, the at least one spring element being effective to deflect and move with the at least one shoe in response to fluid pressure applied to the at least one shoe by a fluid stream to assist in the creation of a primary seal of the circumferential gap between the first and second machine components; wherein the primary seal comprises a groove positioned along a radially inward position of the primary seal; a mid plate comprising a groove, the mid plate extending into
  • FIG. 1 is an exploded view of a seal assembly of an exemplary embodiment of the present invention
  • FIG. 2 is an end view of a portion of an exemplary embodiment of the present invention.
  • FIG. 3 is an elevational view of a portion of an exemplary embodiment of seal assembly
  • FIG. 4 is an elevational view of a portion of an exemplary embodiment of the present invention.
  • FIG. 5 is an end view of a portion of an exemplary embodiment of the present invention.
  • FIG. 6 is an elevational view of a portion of an exemplary embodiment of the present invention.
  • FIG. 7 is an elevational view of a portion of an exemplary embodiment of the present invention.
  • FIG. 8 is an elevational view of a portion of an exemplary embodiment of the present invention.
  • FIG. 9 is an elevational view of a portion of an exemplary embodiment of the present invention.
  • FIG. 10 is a detailed end view of a portion of an exemplary embodiment of the present invention.
  • an embodiment of the present invention provides a seal assembly for sealing a circumferential gap between a first machine component and a second machine component which is rotatable relative to the first machine component about a longitudinal axis.
  • the seal assembly includes a seal carrier, a primary seal, a mid plate, at least one secondary seal, and a front plate.
  • the at least one secondary seal includes at least one sealing element.
  • the at least one secondary seal includes an extension segment extending out in the direction of the primary seal.
  • the primary seal includes a groove positioned along a radially inward position of the primary seal. The extension segment of the secondary seal extends into the groove of the primary seal in a mechanical fit.
  • Turbomachinery typically includes a compressor section, a combustor, and a turbine section.
  • the compressor section ingests ambient air and compresses it.
  • the compressed air from the compressor section enters one or more combustors in the combustor section.
  • the compressed air is mixed with fuel in the combustors, and an air-fuel mixture is combusted in the combustors to form a hot working gas.
  • the hot working gas is routed to the turbine section, where it is expanded through alternating rows of stationary airfoils and rotating airfoils, and used to generate power that can drive a rotor.
  • the expanded gas exiting the turbine section then exhausts from the engine via an exhaust section.
  • the compressor and turbine sections may include several locations in which there may be gaps, or clearances, between the rotating and stationary components.
  • system loss may occur through fluid leakage through clearances in the compressor and turbine sections. This system loss decreases the operational efficiency of the system.
  • An example of the flow leakage is across a clearance between the tips of rotating blades and a surrounding stationary structure or boundary, such as an outer shroud or a vane carrier.
  • Seals are necessary to prevent leakage across areas within the gas turbine engine. Traditionally, a non-contact seal does not retain secondary seals well within the seal assembly. A non-contact seal with better support and retainment of secondary seals is desired.
  • FIG. 1 shows an exploded view of a seal assembly 10 embodiment that may be included in turbomachinery, such as a gas turbine.
  • FIG. 2 shows the seal assembly 10 in its assembled form.
  • the seal assembly 10 may include a front plate 12, at least one secondary seal 14, a mid plate 22, a primary seal 26, and a seal carrier 36.
  • the assembled seal assembly 10 illustrated in FIG. 2 creates a non-contact seal of a circumferential gap 11 between two components, a first machine component 38 and a second machine component, such as a fixed stator 72 and a rotating rotor 48.
  • Each seal assembly 10 includes at least one, and in some situations, a plurality of circumferentially spaced shoes 28 that are located in a non-contact position along an exterior surface of the rotor 48, as part of the primary seal 26.
  • Each shoe 28 has a sealing surface 70 and a slot 30 that extends radially inward toward the sealing surface 70 as can be seen in FIG. 1.
  • the at least one shoe 28 is formed with two or more projections 84, or fins, relative to one of the machine components, and is the bottom portion of the primary seal 26, as can be seen in FIG. 5.
  • the term“axial” or“axially spaced” refers to a direction along the longitudinal axis 42 of the stator 72 and rotor 48, whereas“radial” refers to a direction perpendicular to the longitudinal axis 42.
  • the seal assembly 10 may extend along a circumferential direction C relative to the turbine longitudinal axis 42.
  • the primary seal 26 may include a number of circumferentially spaced spring elements, or at least one spring element 34, as can be better seen in FIG. 7.
  • Each spring element 34 is formed with an inner band 52, and an outer band 54 radially outwardly spaced from the inner band 52.
  • One end of each of the bands 52 and 54 is mounted to, or integrally formed with, the stator 72 and the opposite end thereof is connected to a first stop 32.
  • the first stop 32 includes a leg 56 which is connected to, or integrally formed with a shoe 28, and an arm 58 opposite to the shoe 28, which may be received within a recess formed in the stator 72.
  • the recess has a shoulder 74 positioned in alignment with the arm 58 of the first stop 32.
  • a second stop 60 is connected to, or integrally formed with, the shoe 28.
  • the second stop 60 is circumferentially spaced from the first stop 32 in a position near the point at which the inner and outer bands 52 and 54 connect to the stator 72.
  • the second stop 60 is formed with a leg 62 and an arm 64.
  • the arm 64 may be received within a recess in the stator 72.
  • the recess has a shoulder 74 positioned in alignment with the arm 64 of the second stop 60.
  • a gap is provided between the arm 58 of the first stop 32, and the shoulder, and between the arm 64 of the second stop 60, and the shoulder, such that the shoe 28 can move radially inwardly relative to the rotor 48.
  • the inward motion mentioned above is limited by engagement of the arms with the shoulders to prevent the shoe 28 from contacting the rotor 48, or exceeding design tolerances for the gap between the two.
  • the arms can also contact the stator 72 in the event that the shoe 28 moves radially outwardly relative to the rotor 48, to limit movement of the shoe 28 in that direction.
  • Embodiments of the seal assembly 10 include at least one secondary seal 14, that includes at least one sealing element 16, or plate. At least one spring member 18 can be positioned radially outward from the plate, as is shown in FIG. 4, along an outer ring surface 20.
  • the at least one sealing element 16 includes two sealing elements 16 oriented side-by-side and positioned so that the plate segments extend into the slot 30 of the at least one shoe 28. The at least one sealing element 16 help to radially deflect and move with the at least one shoe 28, in response to the application of fluid pressure to the at least one shoe 28, in a way that assists in the creation of a secondary seal 14 of the circumferential gap 11 between the first and second machine components 38 and 40.
  • the at least one secondary seal 14 includes an aft secondary seal 74 and a forward secondary seal 76 that may be identical and reversed at assembly.
  • Each of the secondary seals 14 may include an extension segment 78 that is along the full portion, or partial portion, of the length of the sealing element 16.
  • the extension segment 78 extends out in the axial direction A.
  • the extension segment 78 along the aft secondary seal 74 can extend towards the primary seal 26, and the extension segment 78 along the forward secondary seal 76 can extend towards a front plate 12.
  • An example of the secondary seal 14 with the extension segment 78 can be seen in FIG. 5.
  • FIG. 6 shows a mid plate 22.
  • the mid plate 22 includes at least one groove 24 along a face of the mid plate 22 extending into the slot 30 formed in the at least one shoe 28, and is positioned between the at least one secondary seal 14 and the at least one shoe 28 of the primary seal 26.
  • the sealing elements 16 of the at least one secondary seal 14 fits into the groove 24 of the mid plate 22.
  • the extension segment 78 from the secondary seal 14 is positioned below the mid plate 22.
  • the extension segment 78 of the at least one secondary seal 14 passes below the mid plate 22 for a mechanical fit with the primary seal 26, securing the at least one secondary seal 14 in [0031]
  • FIG. 3 shows the front plate 12.
  • the front plate 12 can be used to cover the components of the seal assembly 10 in the axial direction A.
  • the seal assembly 10 may include having the at least one secondary seal clamped between the front plate 12 and the mid plate 22.
  • the primary seal 26 may support the inner diameter of the secondary seal 14, and the mid plate 22 can support the outer diameter of the secondary seal 14.
  • the spring member 18 of the secondary seal 14 may react against the mid plate 22.
  • FIG. 6 shows a seal carrier 36.
  • the seal carrier 36 holds all the components of the seal assembly 10 together along a radially outward position of a radially outer ring 50 of the seal carrier 36.
  • the seal carrier 36 in these embodiments, has a protruding edge 68 that extends radially inward that aligns with the cutouts 66 of the other components to help the components to stay in the relative area.
  • the secondary seals 14 include extension segments 78 to reduce wear concerns of the secondary seal 14 and to facilitate ease of assembly.
  • the primary seal 26 includes a groove 82 to provide space for the extension segments 78 of the secondary seals 14 to settle.
  • the groove 82 is positioned along a radially inward position of the primary seal 26. The secondary seals 14 can be rolled into the groove 82 provided in the primary seal 26 prior to the installation of the assembly.
  • the groove 82 can be in a T- shape, for example, with the extension segments 78 fitting into the T-shaped groove 82 provided in the primary seal 26.
  • the exact shape of the groove 82 determines how much play may be allowed from the secondary seals 14.
  • Other shapes of the extension segments 78 and groove 82 can be made to allow for the securing of the secondary seals 14 by the primary seal 26.
  • the extension segments 78 of the at least one secondary seal 14 also help in the installation of the seal assembly 10, since the secondary seal 14 can limited in its movement.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Devices (AREA)

Abstract

L'invention concerne un ensemble joint d'étanchéité (10) destiné à rendre étanche un espace circonférentiel (11) entre un premier élément de machine (38) et un second élément de machine (40) qui est rotatif par rapport au premier élément de machine (38) autour d'un axe longitudinal (42). L'ensemble joint d'étanchéité (10) comprend un support d'étanchéité (36), un joint primaire (26), une plaque médiane (22), au moins un joint secondaire (14), et une plaque avant (12). Ledit joint secondaire (14) comprend au moins un élément d'étanchéité (16). Ledit joint secondaire (14) comprend un segment d'extension (78) s'étendant hors de la direction du joint primaire (26). Le joint primaire (26) comprend une rainure (82) positionnée le long d'une position radialement vers l'intérieur du joint primaire (26). Le segment d'extension (78) du joint secondaire (14) s'étend dans la rainure (82) du joint primaire (26) dans un ajustement mécanique.
PCT/US2018/049534 2018-09-05 2018-09-05 Joint d'étanchéité sans contact à ajustement mécanique Ceased WO2020050835A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US2018/049534 WO2020050835A1 (fr) 2018-09-05 2018-09-05 Joint d'étanchéité sans contact à ajustement mécanique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2018/049534 WO2020050835A1 (fr) 2018-09-05 2018-09-05 Joint d'étanchéité sans contact à ajustement mécanique

Publications (1)

Publication Number Publication Date
WO2020050835A1 true WO2020050835A1 (fr) 2020-03-12

Family

ID=63684547

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2018/049534 Ceased WO2020050835A1 (fr) 2018-09-05 2018-09-05 Joint d'étanchéité sans contact à ajustement mécanique

Country Status (1)

Country Link
WO (1) WO2020050835A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2024194569A1 (fr) * 2023-03-23 2024-09-26 Safran Aircraft Engines Joint d'etancheite de turbomachine

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04347066A (ja) * 1991-05-21 1992-12-02 Toshiba Corp ブラシシール装置
US5181728A (en) * 1991-09-23 1993-01-26 General Electric Company Trenched brush seal
US20020000694A1 (en) * 2000-04-03 2002-01-03 Justak John F. Robust hydrodynamic brush seal
US6364316B1 (en) * 1999-02-11 2002-04-02 Honeywell International Inc. Dual pressure balanced noncontacting finger seal
WO2004053365A1 (fr) * 2002-12-07 2004-06-24 Cross Manufacturing Company (1938) Limited Assemblage joint
US20080008593A1 (en) * 2006-07-06 2008-01-10 Siemens Power Generation, Inc. Turbine blade self locking seal plate system
EP2615257A2 (fr) * 2012-01-13 2013-07-17 General Electric Company Support de joint hybride
US20160109025A1 (en) * 2014-10-21 2016-04-21 United Technologies Corporation Seal ring
US20160130963A1 (en) * 2014-11-07 2016-05-12 United Technologies Corporation Gas turbine engine and seal assembly therefore
EP3133239A1 (fr) * 2015-08-19 2017-02-22 United Technologies Corporation Agencement pour équipement rotatif et system de propulsion d'avion
EP3133240A1 (fr) * 2015-08-19 2017-02-22 United Technologies Corporation Ensemble de joint d'étanchéité sans contact pour équipement rotatif
EP3290646A1 (fr) * 2016-08-29 2018-03-07 United Technologies Corporation Joint d'étanchéité flottant sans contact à faisceaux coudés

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04347066A (ja) * 1991-05-21 1992-12-02 Toshiba Corp ブラシシール装置
US5181728A (en) * 1991-09-23 1993-01-26 General Electric Company Trenched brush seal
US6364316B1 (en) * 1999-02-11 2002-04-02 Honeywell International Inc. Dual pressure balanced noncontacting finger seal
US20020000694A1 (en) * 2000-04-03 2002-01-03 Justak John F. Robust hydrodynamic brush seal
WO2004053365A1 (fr) * 2002-12-07 2004-06-24 Cross Manufacturing Company (1938) Limited Assemblage joint
US20080008593A1 (en) * 2006-07-06 2008-01-10 Siemens Power Generation, Inc. Turbine blade self locking seal plate system
EP2615257A2 (fr) * 2012-01-13 2013-07-17 General Electric Company Support de joint hybride
US20160109025A1 (en) * 2014-10-21 2016-04-21 United Technologies Corporation Seal ring
US20160130963A1 (en) * 2014-11-07 2016-05-12 United Technologies Corporation Gas turbine engine and seal assembly therefore
EP3133239A1 (fr) * 2015-08-19 2017-02-22 United Technologies Corporation Agencement pour équipement rotatif et system de propulsion d'avion
EP3133240A1 (fr) * 2015-08-19 2017-02-22 United Technologies Corporation Ensemble de joint d'étanchéité sans contact pour équipement rotatif
EP3290646A1 (fr) * 2016-08-29 2018-03-07 United Technologies Corporation Joint d'étanchéité flottant sans contact à faisceaux coudés

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2024194569A1 (fr) * 2023-03-23 2024-09-26 Safran Aircraft Engines Joint d'etancheite de turbomachine
FR3146941A1 (fr) * 2023-03-23 2024-09-27 Safran Aircraft Engines Joint d’étanchéité de turbomachine

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