WO2018089014A1 - Assemblage joint entre un conduit de transition et un étage d'une structure d'aube de turbine - Google Patents

Assemblage joint entre un conduit de transition et un étage d'une structure d'aube de turbine Download PDF

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Publication number
WO2018089014A1
WO2018089014A1 PCT/US2016/061579 US2016061579W WO2018089014A1 WO 2018089014 A1 WO2018089014 A1 WO 2018089014A1 US 2016061579 W US2016061579 W US 2016061579W WO 2018089014 A1 WO2018089014 A1 WO 2018089014A1
Authority
WO
WIPO (PCT)
Prior art keywords
biasing
seal assembly
seal
assembly
gas turbine
Prior art date
Application number
PCT/US2016/061579
Other languages
English (en)
Inventor
Chad W. Heinrich
Stephen A. Camillieri
Christian K. Funk
Jacob Williams HARDES
Daniel CASSAR
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to PCT/US2016/061579 priority Critical patent/WO2018089014A1/fr
Publication of WO2018089014A1 publication Critical patent/WO2018089014A1/fr

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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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings

Definitions

  • Disclosed embodiments are generally related to a combustion turbine engine, and, more particularly, to a seal assembly between a transition duct and a stage one turbine vane structure.
  • a combustion turbine engine such as a gas turbine engine, includes for example a compressor section, a combustor section and a turbine section. Intake air is
  • FIG. 1 shows a cross-sectional view of one non-limiting embodiment of a disclosed seal assembly between a transition duct and a stage one turbine vane structure.
  • FIG. 2 shows a perspective view of one non-limiting embodiment of a disclosed seal assembly.
  • FIG. 3 is a front view of seal segments arranged to form a segmented annular seal assembly.
  • FIG. 4 shows a perspective view of another non-limiting embodiment of a disclosed seal assembly.
  • the present inventors have recognized certain issues in connection with certain known seals between a transition duct and a first stage turbine vane structure. Often, such seals may involve separate seal structures that can result in a relatively large radial gap between the transition and the vane structure, and such a relatively large gap may not be conducive to reducing leakage of compressed air into the hot flow of combustion gases. This relatively large gap in turn leads to a correspondingly large gap volume, which may not be conducive to reducing the amount of purged air utilized for cooling structures involved in the interface between the transition and the vane structure.
  • the present inventors propose an innovative seal assembly that is effective for reducing such a radial gap and thus conducive to reducing such leakage.
  • This gap reduction is further effective for reducing the volume of the gap, which in turn reduces the amount of purging air utilized for cooling the structures involved in the interface between the transition and the vane structure.
  • the proposed seal assembly is effective to increase the sealing area between the transition and the vane structure. This increase in sealing area in turn reduces the size of possible paths through which leakage could develop, and thus contributing to engine efficiency by reducing total engine leakage.
  • displacements such as axial, radial, or circumferential displacements, that can develop between the transition duct and the first stage turbine vane structure during operation of the gas turbine engine. It will be appreciated that combinations of such displacements, if not appropriately accommodated, could result in excessive twisting or bending of the structures subject to such displacements. Compliant acceptance of such displacements permits relatively more relative motion between the transition duct and the first stage turbine vane structure without undesirable mechanical distress, and thus the proposed seal assembly is expected to last longer in operation without malfunctions. Accordingly, in a cost-effective and reliable manner, the proposed seal assembly is expected to result in relatively lower levels of stress to the seal assembly and associated structures, with a concomitant reduction in wear and cracking, which is conducive to a more reliable and longer-lasting seal assembly.
  • FIG. 1 shows a cross-sectional view of one non-limiting embodiment of a disclosed seal assembly 10 between a transition duct 12 and a stage one turbine vane structure 14. Seal assembly 10 is arranged to seal a gap between transition duct 12 extending between a combustor (not shown) of a gas turbine engine and first stage turbine vane structure 14.
  • connection member 16 may be arranged at a first side 18 of seal assembly 10 for connecting, for example, to a transition outlet ring 20 of transition duct 12.
  • a connection member 22 may be arranged at a second side 24 of seal assembly 10 opposed to first side 18 of the seal assembly for connecting to the first stage turbine vane structure 14, such as a vane shroud.
  • connection members 16, 22 may comprise protrusions, which are respectively insertable into appropriately configured cutouts in transition outlet ring 20 and first stage turbine vane structure 14.
  • Respective retainers 19 may be used to secure connection members 16, 22 into the respective receiving cutouts constructed in transition outlet ring 20 and first stage turbine vane structure 14.
  • a flexible seal element 26 extends between opposed sides 18, 24 of seal assembly 10 in a first zone of the gas turbine engine subject to a first pressure load, schematically represented by arrows 33 in FIG. 1 .
  • this zone may comprise air compressed in the compressor section of the engine that may be conveyed to an air plenum fluidly coupled to the transition system for cooling/purging purposes.
  • FIG. 1 indicates a coordinate system comprising an axis 23, which corresponds to a longitudinal axis of the seal assembly, an axis 25 which corresponds to a radial axis relative to a circumferential axis 27 of the seal assembly.
  • Flexible seal element 26 may be a cloth seal, such as without limitation may comprise a high temperature-resistant material, such as metal, ceramic or polymer fibers which may be woven, knitted or otherwise pressed into a layer of fabric. If the seal cloth involves two or more layers of cloth, depending on the needs of a given application, the multiple doth layers may be appropriately tailored. For example, different materials may be chosen for the multiple layers, the construction may be different for the multiple layers or different thicknesses may be chosen for the multiple layers. In one non-limiting embodiment, the cloth seal may involve a Dutch twill weave cloth assembly, as may be formed of a high temperature cobalt-based superalloy, such as without limitation Haynes 188 alloy.
  • a biasing assembly 28 is disposed between opposed sides 18, 24 of seal assembly 10 in a second zone of the gas turbine engine subject to a second pressure load different than the first pressure load.
  • this zone may allow passage to the hot flow of combustion gases, schematically represented by arrows 35 in FIG. 1 and would be at a relatively lower pressure than the first zone of the gas turbine engine subject to the first pressure load.
  • Biasing assembly 28 is arranged to compliantly accept the various displacements that can occur between transition duct 12 and first stage turbine vane structure 14 during operation of the gas turbine engine. Biasing assembly 28 is further arranged to provide mechanical support to flexible seal element 26 so that flexible seal element 26 can withstand the pressure load differential between the first and the second zones of the gas turbine engine.
  • biasing assembly 28 may include a first biasing element 32 including a first portion 34 (e.g., a straight portion), disposed onto a corresponding portion of a radially inwardly surface 36 of flexible seal element 26 and extending axially from first side 18 of seal assembly 10 to a first location 38 between opposed sides 18, 24 of the seal assembly, and further includes a second portion 40 extending from first portion 34 of first biasing element 32 to define a biasing segment 42 of first biasing element 32.
  • first portion 34 e.g., a straight portion
  • Biasing assembly 28 may further include a second biasing element 44
  • first biasing element 32 (structurally similar to first biasing element 32, such as forming respective spring clips) including a first portion 46 (e.g., a straight portion) disposed onto a corresponding portion of radially inwardly surface 36 of flexible seal element 26 and extending axially from second side 24 of seal assembly 10 to a second location 48 between opposed sides 18, 24 of seal assembly 10, and further includes a second portion 50 extending from first portion 46 of second biasing element 44 to define a biasing segment 52 of second biasing element 44.
  • Respective biasing segments 42, 52 of first and second biasing elements 32, 44 are arranged to mutually engage one another at a location radially away (e.g., radially inwardly) from flexible seal element 26.
  • biasing elements 32, 44 may be made of a multi-ply construction, such as IN X-750 sheet metal, which may be heat treated to meet any desired spring properties. This and other materials that have suitable spring and thermal resistance qualities may be used in various embodiments of biasing elements 32, 44. It will be appreciated that respective first and second portions 34, 40 of first biasing element 32 may (but need not) comprise a respective unitary construction.
  • respective first and second portions 46, 50 of second biasing element 44 may also (but need not) comprise a respective unitary construction.
  • a radially outer surface 60 of a respective one of biasing segments engages a corresponding radially inner surface 62 of the other respective one of the biasing segments (e.g., first biasing element 32 in FIG. 1 ) to establish a mutually opposed urging interface between the engaging surfaces of respective biasing elements 32, 44.
  • the respective biasing segments 42, 52 of first and second biasing elements 32, 44 comprise respective curvilinear segments relative to longitudinal axis 23.
  • FIG. 2 shows a perspective view of one non-limiting embodiment of a disclosed seal assembly illustrating affixing means 21 (such as spot welds, etc) for connecting flexible seal element 26 to biasing assembly 28.
  • affixing means 21 such as spot welds, etc
  • FIG. 3 is a front view of arcuate seal segments 10A through 10F arranged to form a segmented annular seal assembly 69. It will be appreciated that the number of seal segments illustrated in FIG. 3 should be construed in an example sense and not in a limiting sense since annular seal assembly 69 may be formed by any number of seal assembly segments, such as one or more seal segments circumferentially
  • respective edges 72, 74 of the respective first portions of the first and second biasing elements are configured to provide an overlapping joint (shiplap joint) between respective adjacent seal assembly segments of the plurality of
  • disclosed embodiments are expected to provide in a cost-effective manner a compliant and robust seal assembly that should provide extended life to associated transition ducts and row 1 vane structures, while also providing more consistent sealing performance.

Landscapes

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

Abstract

L'invention concerne un assemblage joint (10) conçu pour sceller un espace entre un conduit de transition (12) d'un moteur à turbine à gaz et une structure d'aube de turbine de premier étage (14). Un élément d'étanchéité souple (26), tel qu'un joint d'étanchéité en tissu, s'étend entre des côtés opposés (18, 24) de l'assemblage joint dans une première zone du moteur à turbine à gaz soumise à une première charge de pression. Un ensemble de sollicitation (28) est disposée entre les côtés opposés de l'assemblage joint dans une seconde zone du moteur de turbine à gaz soumise à une seconde charge de pression différente de la première charge de pression. L'ensemble de sollicitation (28) est conçu pour accepter de manière complémentaire des déplacements qui se produisent entre le conduit de transition et la structure d'aube de turbine de premier étage pendant le fonctionnement du moteur à turbine à gaz. L'ensemble de sollicitation (28) est en outre conçu pour fournir un support mécanique à l'élément d'étanchéité souple (26) de sorte qu'il puisse résister à un différentiel de charge de pression entre les première et seconde zones du moteur à turbine à gaz.
PCT/US2016/061579 2016-11-11 2016-11-11 Assemblage joint entre un conduit de transition et un étage d'une structure d'aube de turbine WO2018089014A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US2016/061579 WO2018089014A1 (fr) 2016-11-11 2016-11-11 Assemblage joint entre un conduit de transition et un étage d'une structure d'aube de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2016/061579 WO2018089014A1 (fr) 2016-11-11 2016-11-11 Assemblage joint entre un conduit de transition et un étage d'une structure d'aube de turbine

Publications (1)

Publication Number Publication Date
WO2018089014A1 true WO2018089014A1 (fr) 2018-05-17

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Family Applications (1)

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PCT/US2016/061579 WO2018089014A1 (fr) 2016-11-11 2016-11-11 Assemblage joint entre un conduit de transition et un étage d'une structure d'aube de turbine

Country Status (1)

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WO (1) WO2018089014A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07293276A (ja) * 1994-04-20 1995-11-07 Mitsubishi Heavy Ind Ltd 燃焼器のスプリングクリップ構造
EP0875721A1 (fr) * 1996-01-17 1998-11-04 Mitsubishi Jukogyo Kabushiki Kaisha Unite a joints elastiques de chambre de combustion
US6547257B2 (en) 2001-05-04 2003-04-15 General Electric Company Combination transition piece floating cloth seal and stage 1 turbine nozzle flexible sealing element
EP2559859A1 (fr) * 2011-08-16 2013-02-20 General Electric Company Fixation d'extrémité de joint
EP2775102A2 (fr) * 2013-03-08 2014-09-10 General Electric Company Dispositif et procédé pour empêcher une fuite d'air entre de multiples composants de turbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07293276A (ja) * 1994-04-20 1995-11-07 Mitsubishi Heavy Ind Ltd 燃焼器のスプリングクリップ構造
EP0875721A1 (fr) * 1996-01-17 1998-11-04 Mitsubishi Jukogyo Kabushiki Kaisha Unite a joints elastiques de chambre de combustion
US6547257B2 (en) 2001-05-04 2003-04-15 General Electric Company Combination transition piece floating cloth seal and stage 1 turbine nozzle flexible sealing element
EP2559859A1 (fr) * 2011-08-16 2013-02-20 General Electric Company Fixation d'extrémité de joint
EP2775102A2 (fr) * 2013-03-08 2014-09-10 General Electric Company Dispositif et procédé pour empêcher une fuite d'air entre de multiples composants de turbine

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