US10385705B2 - Gas turbine engine having a vane assembly - Google Patents

Gas turbine engine having a vane assembly Download PDF

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Publication number
US10385705B2
US10385705B2 US15/147,954 US201615147954A US10385705B2 US 10385705 B2 US10385705 B2 US 10385705B2 US 201615147954 A US201615147954 A US 201615147954A US 10385705 B2 US10385705 B2 US 10385705B2
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United States
Prior art keywords
face
opening
support surface
extending
rail
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US15/147,954
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English (en)
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US20170321560A1 (en
Inventor
Peter Balawajder
Benjamin F. Hagan
Jeffrey Michael Jacques
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RTX Corp
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United Technologies Corp
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Priority to US15/147,954 priority Critical patent/US10385705B2/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BALAWAJDER, Peter, JACQUES, Jeffrey Michael, HAGAN, BENJAMIN F.
Priority to EP17159421.1A priority patent/EP3244020B1/de
Publication of US20170321560A1 publication Critical patent/US20170321560A1/en
Application granted granted Critical
Publication of US10385705B2 publication Critical patent/US10385705B2/en
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CHANGE OF NAME Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS. Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RTX CORPORATION reassignment RTX CORPORATION CHANGE OF NAME Assignors: RAYTHEON TECHNOLOGIES CORPORATION
Active legal-status Critical Current
Adjusted expiration legal-status Critical

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • Gas turbine engines are provided with a plurality of vanes such as turbine vanes or compressor vanes.
  • the vanes are stationary and direct a flow of gases against airfoils of rotating turbine blades or compressor blades.
  • the vanes include a mounting rail that is solid and fairly stiff.
  • the mounting rail is generally disposed away from the flow path of the gases that are directed by the vanes.
  • the mounting rail may experience high stresses that may lead to a life shortfall of the vane.
  • the first opening includes a first side surface extending from the first face towards a first support surface, a second side surface disposed opposite the first side surface extending from the first face towards a second support surface, and a first opening surface extending between the first side surface and the second side surface, the first opening surface extending from the first face towards a third support surface that extending between the first support surface and the second support surface.
  • the first rail defines a second opening extending from the second face towards the first face.
  • the second opening includes a third side surface extending from the second face towards a fourth support surface, a fourth side surface disposed opposite the third side surface extending from the second face towards a fifth support surface, and a second opening surface extending from the second face towards a sixth support surface.
  • a seal is received within a slotted region disposed between the first support surface, the second support surface, the third support surface, the fourth support surface, the fifth support surface, and the sixth support surface.
  • the seal has a seal body extending between a first seal face and a second seal face.
  • the first rail defines a first opening extending from the first face towards the second face.
  • the first opening is spaced apart from the second opening by the slotted region.
  • the seal has a seal body extending between a first seal end and a second seal end.
  • FIG. 2 is a partial side view of a vane assembly attached to a case of the gas turbine engine
  • FIG. 3 is a partial front view of the vane assembly
  • the outer platform 50 is disposed proximate the case.
  • the inner platform 52 is spaced apart from and is disposed opposite the outer platform 50 .
  • the vane 54 is configured as an airfoil that extends between the outer platform 50 and the inner platform 52 .
  • the outer platform 50 includes a first rail 60 and a second rail 62 .
  • the first rail 60 extends from the outer platform 50 towards the case.
  • the first rail 60 is disposed proximate the first end 42 of the vane assembly 40 .
  • the first rail 60 acts as a pressure wall that takes a pressure drop across the vane assembly 40 .
  • the first opening 78 includes a first side surface 110 , a second side surface 112 , and a first opening surface 114 .
  • the first side surface 110 extends from the first face 70 to the first support surface 100 .
  • the second side surface 112 is disposed opposite the first side surface 110 .
  • the second side surface 112 extends from the first face 70 to the second support surface 102 .
  • the first opening surface 114 extends between the first side surface 110 and the second side surface 112 .
  • the first opening surface 114 extends from the first face 70 to the third support surface 104 .
  • the first opening 78 has a first width.
  • the fourth support surface 120 , the fifth support surface 122 , and the sixth support surface 124 are spaced apart from the first support surface 100 , the second support surface 102 , and the third support surface 104 .
  • the fourth support surface 120 , the fifth support surface 122 , and the sixth support surface 124 are disposed substantially parallel to the first support surface 100 , the second support surface 102 , and the third support surface 104 .
  • the fourth support surface 120 , the fifth support surface 122 , and the sixth support surface 124 are disposed substantially parallel to the second face 72 and the first face 70 .
  • the first opening 78 is spaced apart from the second opening 80 by the slotted region 82 .
  • Slotted region 82 is defined between the first support surface 100 , the second support surface 102 , the third support surface 104 , the fourth support surface 120 , the fifth support surface 122 , and the sixth support surface 124 .
  • the slotted region 82 has a slotted region width that is greater than the first width.
  • the second rail 62 is disposed proximate the second end 44 of the vane assembly 40 .
  • the second rail 62 extends from the outer platform 50 towards the case.
  • the second rail 62 may be provided with the first opening 78 , the second opening 80 , and the slotted region 82 disposed between the first opening 78 and the second opening 80 .
  • the first opening 78 , the second opening 80 , and the slotted region 82 may have a substantially similar configuration as previously described.
  • attachment shall be interpreted to mean that a structural component or element is in some manner connected to or contacts another element, either directly or indirectly through at least one intervening structural element, or is integrally formed with the other structural element.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US15/147,954 2016-05-06 2016-05-06 Gas turbine engine having a vane assembly Active 2037-09-23 US10385705B2 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US15/147,954 US10385705B2 (en) 2016-05-06 2016-05-06 Gas turbine engine having a vane assembly
EP17159421.1A EP3244020B1 (de) 2016-05-06 2017-03-06 Gasturbinenmotor mit einer leitschaufelanordnung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15/147,954 US10385705B2 (en) 2016-05-06 2016-05-06 Gas turbine engine having a vane assembly

Publications (2)

Publication Number Publication Date
US20170321560A1 US20170321560A1 (en) 2017-11-09
US10385705B2 true US10385705B2 (en) 2019-08-20

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US15/147,954 Active 2037-09-23 US10385705B2 (en) 2016-05-06 2016-05-06 Gas turbine engine having a vane assembly

Country Status (2)

Country Link
US (1) US10385705B2 (de)
EP (1) EP3244020B1 (de)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3111162B1 (fr) * 2020-06-04 2022-06-24 Safran Aircraft Engines Soudure avec languette d’étanchéité
JP2021195920A (ja) 2020-06-16 2021-12-27 東芝エネルギーシステムズ株式会社 タービン静翼
US11814991B1 (en) * 2022-07-28 2023-11-14 General Electric Company Turbine nozzle assembly with stress relief structure for mounting rail
US11885241B1 (en) 2022-07-28 2024-01-30 General Electric Company Turbine nozzle assembly with stress relief structure for mounting rail

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1793088A2 (de) 2005-11-30 2007-06-06 General Electric Company Verfahren und Vorrichtung zur Montierung von Gasturbinenleitschaufeln .
US20070166154A1 (en) * 2004-07-14 2007-07-19 Power Systems Mfg., Llc Vane platform rail configuration for reduced airfoil stress
US20080148737A1 (en) * 2006-12-21 2008-06-26 Power Systems Manufacturing, Llc Turbine Static Structure for Reduced Leakage Air
US20090074562A1 (en) 2003-12-12 2009-03-19 Self Kevin P Nozzle guide vanes
GB2462268A (en) 2008-07-30 2010-02-03 Siemens Ag A segment of an annular guide vane assembly comprising a cut-out with a seal block within
WO2016021330A1 (ja) 2014-08-04 2016-02-11 三菱日立パワーシステムズ株式会社 静翼、ガスタービン、分割環、静翼の改造方法、および、分割環の改造方法
US20160047259A1 (en) 2013-04-11 2016-02-18 United Technologies Corporation Gas turbine engine stress isolation scallop

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2462268A (en) * 1947-05-01 1949-02-22 Kahi Joseph Locking means for a hinged impact mass or weight for marine equipment

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090074562A1 (en) 2003-12-12 2009-03-19 Self Kevin P Nozzle guide vanes
US20070166154A1 (en) * 2004-07-14 2007-07-19 Power Systems Mfg., Llc Vane platform rail configuration for reduced airfoil stress
EP1793088A2 (de) 2005-11-30 2007-06-06 General Electric Company Verfahren und Vorrichtung zur Montierung von Gasturbinenleitschaufeln .
US20080148737A1 (en) * 2006-12-21 2008-06-26 Power Systems Manufacturing, Llc Turbine Static Structure for Reduced Leakage Air
GB2462268A (en) 2008-07-30 2010-02-03 Siemens Ag A segment of an annular guide vane assembly comprising a cut-out with a seal block within
US20160047259A1 (en) 2013-04-11 2016-02-18 United Technologies Corporation Gas turbine engine stress isolation scallop
WO2016021330A1 (ja) 2014-08-04 2016-02-11 三菱日立パワーシステムズ株式会社 静翼、ガスタービン、分割環、静翼の改造方法、および、分割環の改造方法

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
European Search Report for European Application No. 17159421.1 dated Apr. 12, 2018; 12 pages.

Also Published As

Publication number Publication date
EP3244020B1 (de) 2020-05-06
EP3244020A2 (de) 2017-11-15
EP3244020A3 (de) 2018-05-16
US20170321560A1 (en) 2017-11-09

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