US3857649A - Inlet vane structure for turbines - Google Patents

Inlet vane structure for turbines Download PDF

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Publication number
US3857649A
US3857649A US00387069A US38706973A US3857649A US 3857649 A US3857649 A US 3857649A US 00387069 A US00387069 A US 00387069A US 38706973 A US38706973 A US 38706973A US 3857649 A US3857649 A US 3857649A
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US
United States
Prior art keywords
radially
vanes
ceramic
shroud ring
support structure
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.)
Expired - Lifetime
Application number
US00387069A
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English (en)
Inventor
R Schaller
S Leshnoff
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CBS Corp
Original Assignee
Westinghouse Electric 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 Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Priority to US00387069A priority Critical patent/US3857649A/en
Priority to NL7409924A priority patent/NL7409924A/nl
Priority to CA205,732A priority patent/CA995141A/en
Priority to IT25717/74A priority patent/IT1017716B/it
Priority to GB3424774A priority patent/GB1470989A/en
Priority to DE2437486A priority patent/DE2437486C2/de
Priority to CH1078474A priority patent/CH585845A5/xx
Priority to JP49090898A priority patent/JPS5228168B2/ja
Priority to FR7427815A priority patent/FR2240355B1/fr
Priority to SE7410246A priority patent/SE392147B/xx
Application granted granted Critical
Publication of US3857649A publication Critical patent/US3857649A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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
    • 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
    • F01D25/005—Selecting particular materials
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics

Definitions

  • ABSTRACT [52] US. Cl 415/200, 415/137, 415/214, An improved inlet vane structure for axial flow tur- 415/217 bines, comprising a plurality of ceramic vanes extend- [51] Fold 9/00, Fold 9/02, Fold 25/26 ing radially outward from an inner shroud ring and [58] Field of Search 415/191, 214, 200, 212, Supportedat their outer end by a blade ring The 115/177, 140,191,1601416/22l241 vanes are held in a compressed state by spring mounted within the outer ends of a vane support 1 Remfllces Cited structure.
  • Tapered vane end caps which are also con- UNITED STATES PATENTS structed of ceramic materials, mate with the vanes and 2,801,076 7/1957 Terrell et a1.
  • 4151200 Provide additional Compressive forces on the vanes 3,025,037 3/1962 Beckstrom 415/177 wh n h vanes r lo ded due o fluid flow 3,619,077 11/1971 Wile et a1.
  • This invention relates to turbines-and more particularly to a support assembly for maintaining first row ceramic inlet guide vanes in a compressed state.
  • Another method of allowing increasing temperatures at the nozzle inlet is to construct the structure from materials that will withstand the high temperatures. Ceramics have long been known to withstand high temperatures, and ceramics are structurally strong when they are utilized in a compressed state. An inlet nozzle structure of ceramics which is maintained in compres sion would obviate the need for both a cooling effect on the nozzles, and the need for cooling equipment.
  • German Patent No. 826,673 issued in January, 1952, shows a turbine inlet being guided by radially directed compressive springs.
  • the springs are used to hold the inlet in circular alignment, and are not utilized to prevent failure of the ceramic inlet nozzle by reducing noncompressive forces.
  • an improved inlet vane structure for a gas turbine.
  • Springs are disposed radially outwards of stationary ceramic inlet vanes and end supports. The springs compress the inlet vanes, through the vane end supports, and allow for aslight pivotable movement during turbine operation.
  • An alternative embodiment of the inlet guide vanes is comprised of ceramic guide vanes that are tapered in the axially downstream direction, that mate with supporting ceramic end caps tapered correspondingly; wherein a downstream flow of fluid would wedge the vane into the end caps creating additional compressive forces within the structure.
  • FIG. 4 is a perspective view of an alternative embodiment of a vane and end caps.
  • FIG. 1 a portion of a gas turbine 10 is shown by a side view of its inlet nozzle arrangement 12.
  • the inlet nozzle 12 includes an inner shroud ring 14 which has a plurality of circumferentially disposed cooling fluid passageways 16 that allows'a cooling fluid to impinge upon an inner supporting structure 17.
  • the inner supporting structure 17 includes a plurality of hemispherically-shaped pivot studs 18 circumferentially disposed on the radially outward side of ring 14.
  • the studs 18 each pivotably mate with a convex hemispherically-shaped nobule 20, providing the inlet nozzle arrangement 12 with a slight freedom of movement.
  • a pair of the nobules 20 are attached to the radially inward side of each ofa plurality of circumferentially disposed inner metal shoes 22.
  • the inner metal shoe 22 is in turn, disposed radially inwards of, and supports an insulator pad 24.
  • Each metal shoe 22 has a radially outwardly directed lip member 26 as shown in FIG. 2, on one of its ends to prevent the insulator pad 24 from moving in a circumferential direction.
  • a jambolt 28 extends through ring 14, engages and further restrains the insulator pad 24.
  • An inner ceramic end cap 34 is disposed on the radially outward side of insulator pad 24.
  • the end cap 34 is permitted a slight circumferential motion with respect to insulator pad 24 because of a tongue 30 and groove 32 arrangement therebetween.
  • the track-like components, the tongue 30 in cap 34 and the groove 32 in insulator pad 24 thereby also provide a slight circumferential movability to the entire inlet structure 12.
  • Each inner end cap 34 has a substantially axially disposed groove 35.
  • Each groove 35 secures the inner end of a radially extending air foil vane 36.
  • Each air foil vane 36 is similarly secured on its radially outward end by a groove 37 in an outer end cap 38.
  • the support structure radially outward of the air foil vane 36 is similar to that radially inward of the vane 36, except that a compressive inducing means is disposed outwardly of vane 36.
  • Each outer end cap 38 has a tongue arrangement 40 which is similar to that of-inner end cap 34.
  • the tongue 40 slidably interlocks with a circumferentially disposed groove 42 on the radially inward side of each outer insulator pad 44.
  • the outer tongue 40 and groove 42 arrangement contributes to the circumferential movement allowable in nozzle inlet structure 12.
  • Each outer insulator pad 44 is disposed in an outer metal shoe 50. The pad 44 is restrained from-circumferential motion by engagement witha jambolt 46 that extends through an outer support ring 48 and by a radially inwardly directed lip 51 as shown in FIG. 2 on one end of shoe 50.
  • the outer shroud ring 48 is coaxial with inner support ring 14, and the two rings 14 and 48 provide the containment for the nozzle.
  • a cooling fluid passageway 49 is directed through the outer shroud ring 48 to allow cooling fluid to impinge upon each outer metal shoe 50.
  • Each outer shoe 50 has a convex hemisphericallyshaped outer nobule 52 attached to its radially outward side.
  • a radially directed plunger 54 has a concave hemispherically-shaped inner end 56 that supports and cooperatively associates with outer nobule 52 to permit shoe 50 to have a movable interface with respect to said plunger 54.
  • the plunger 54 is slidably held in its radial direction by a sleeve member 58 that is integral with and supported by, outer shroud ring 48.
  • a bias producing spring member 60 cooperates with plunger 54 to provide a radially inwardly directed compressive force upon inlet nozzle members 34, 36 and 38, which are constructed from ceramic materials. The compressive force upon these ceramic members 34, 36 and 38 prevents the inlet structure from failing under extremely high temperatures.
  • each outer insulator pad 44 retainstwo vane outer end caps 38 and 38'.
  • Each inner insulator pad 24 likewise retains two inner end caps, 34
  • Each end cap, 34 and 38 supports an end of only one air foil vane 36.
  • the radially directed lip members, 26 and 51, extending off one end inner shoes 22and outer shoes 50 respectively, are shown in- FIG. 2, each restraining their respective insulator pads, 24 or 44, from circumferential motion.
  • a portion of the outer ring member 48 is shown in the radially inwardly directed view of FIG. 3.
  • FIG. 4 The ceramic elements of this invention are shown in an alternative embodiment of FIG. 4.
  • An inner end cap 62 is shown tapered to increasing thickness in the downstream direction.
  • Cap 62 has a circumferentially disposed tongue 64 on its radially inward side similar to the tongue arrangement 30 of inner-end cap 34 shown in FIG. 1.
  • End cap 62 has an inclined plane 68 in which a serpentine round bottomed groove 66 is disposed.
  • a ceramic air foil vane 72 has a correspondingly rounded radially inner end 70 that mates with groove 66 and matches its configuration.
  • the ceramic air foil vane 72 is tapered to decreasing downstream lengthwise dimensions, and has a radially outer end .74 that is rounded similar to inner end 70.
  • a ceramic outer end cap 80 is disposed radially outwardly of the mates with the radially outward end'74 of vane 72 through a serpentine round bottomed groove 76 disposed on an inclined plane 78 of cap 80 similar to that-of inner end cap 62.
  • the outerceramic end cap 80 inclined in the direction of increasing thickness downstream has a tongue 82 arrangement similar to that of outer end cap 38 shown in FIG. 1.
  • the inner and outer round bottomed grooves 66 and 76 cooperatively mate with the inner and outer rounded ends 70 and 74 of the radially directed tapered ceramic air foil vane 72.
  • the configuration allows the air foil vane 72 to move relative to the end caps 62 and 80.
  • the ceramic components, the vane 72, and end caps '62 and 80 will have minimum stress concentrations that would be caused by thermal expansion, mismatch, imperfectly joined parts, or notch effects.
  • Ceramic materials of the type used in this invention aregencrally silicon nitride Si N,, or silicon carbide SiC. Their desirability comes from the fact that the raw materials are very inexpensive, that they can withstand very high temperatures and they resist most forms of deterioration.
  • An inlet nozzle for a gas turbine comprising:
  • a radially inner shroud ring a radially outer shroud ring coaxial with said radially inner shroud ring.
  • a plurality of radially extending ceramic vane structures disposed between said radially inner and said radially outer shroud rings, each of said vanes being secured at one end to said radially inner shroud ring by an inner support structure, each of said vanes being secured at its other end to said radially outer shroud ring by an outer support structure,
  • said inner support structure comprising a ceramic end cap, an insulator pad and an'inner shoe plate disposed on said inner shroud ring,
  • said outer support structure comprising a ceramic end cap, an insulator pad, an outer shoe plate and a bias producing means
  • said outer shoe plate being movable connected to said bias producing means, said bias producing means reacting cooperatively with said outer ring, wherein said bias producing means provides a compressive force directed radially inwardly on each of said ceramic structures,
  • said bias producing means consists of a rod-like plunger cooperatively associated with a spring member to induce a compressive force upon said ceramic structure, said plunger having a hemispherical surface on its inner end to provide a movable interface with respect to said outer shoe which has a mating hemispherical surface.
  • An inlet nozzle for a gas turbine comprising:
  • a radially inner shroud ring a radially outer shroud ring coaxial with said radially inner shroud ring, a plurality of radially extending ceramic vane structures disposed between said radially inner and said radially outer shroud rings, each of said vanes being secured at one end to said radially inner shroud ring by an inner support structure, each of said vanes being secured at its other end to said radially outer shroud ring by an outer support structure,
  • said inner structure comprising a ceramic end cap, an insulator pad and aninsulator plate disposed on said inner shroud ring,
  • said outer support structure comprising a ceramic end cap, an insulator pad, an outer shoe plate and a bias producing means
  • said outer shoe plate being movably connected to said bias producing means, said bias producing means reactingcooperatively with said outer ring, wherein said bias producing means provides a compressive force directed radially inwardly on each of said ceramic structures,
  • said end caps having rounded grooves, said end caps having increasing thickness in the downstream direction, said vanes having'their inner and outer ends rounded to mate with said rounded grooves in said end caps, to provide additional compressive forces on said ceramic structures due to the fluid load upon said vanes in thedirection of elastic fluid flow.
  • An inlet nozzle for a gas turbine comprising:
  • each of said vanes being secured at one end to said radially inner shroud ring by an inner support structure, each of said vanes being secured at its other end to said radially outer shroud ring by an outer support structure,
  • said inner support structure comprising an inner ceramic end cap
  • said outer support structure comprising an outer ceramic end cap

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00387069A 1973-08-09 1973-08-09 Inlet vane structure for turbines Expired - Lifetime US3857649A (en)

Priority Applications (10)

Application Number Priority Date Filing Date Title
US00387069A US3857649A (en) 1973-08-09 1973-08-09 Inlet vane structure for turbines
NL7409924A NL7409924A (nl) 1973-08-09 1974-07-23 Inlaatschoepconstructie voor turbines.
CA205,732A CA995141A (en) 1973-08-09 1974-07-26 Inlet vane structure for turbines
IT25717/74A IT1017716B (it) 1973-08-09 1974-07-30 Struttura di palette direttrici d ingresso per turbine
GB3424774A GB1470989A (en) 1973-08-09 1974-08-02 Inlet vane structurefor turbines
DE2437486A DE2437486C2 (de) 1973-08-09 1974-08-03 Düsenanordnung für eine Gasturbine
CH1078474A CH585845A5 (nl) 1973-08-09 1974-08-07
JP49090898A JPS5228168B2 (nl) 1973-08-09 1974-08-09
FR7427815A FR2240355B1 (nl) 1973-08-09 1974-08-09
SE7410246A SE392147B (sv) 1973-08-09 1974-08-09 Gasturbin med ett inloppsmunstycke

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00387069A US3857649A (en) 1973-08-09 1973-08-09 Inlet vane structure for turbines

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US3857649A true US3857649A (en) 1974-12-31

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US00387069A Expired - Lifetime US3857649A (en) 1973-08-09 1973-08-09 Inlet vane structure for turbines

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US (1) US3857649A (nl)
JP (1) JPS5228168B2 (nl)
CA (1) CA995141A (nl)
CH (1) CH585845A5 (nl)
DE (1) DE2437486C2 (nl)
FR (1) FR2240355B1 (nl)
GB (1) GB1470989A (nl)
IT (1) IT1017716B (nl)
NL (1) NL7409924A (nl)
SE (1) SE392147B (nl)

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USB552006I5 (nl) * 1975-02-24 1976-02-03
USB563412I5 (nl) * 1975-03-28 1976-02-24
US3966353A (en) * 1975-02-21 1976-06-29 Westinghouse Electric Corporation Ceramic-to-metal (or ceramic) cushion/seal for use with three piece ceramic stationary vane assembly
US4008978A (en) * 1976-03-19 1977-02-22 General Motors Corporation Ceramic turbine structures
US4076451A (en) * 1976-03-05 1978-02-28 United Technologies Corporation Ceramic turbine stator
US4180371A (en) * 1978-03-22 1979-12-25 Avco Corporation Composite metal-ceramic turbine nozzle
US4552509A (en) * 1980-01-31 1985-11-12 Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for joining two relatively rotatable turbomachine components
US4768924A (en) * 1986-07-22 1988-09-06 Pratt & Whitney Canada Inc. Ceramic stator vane assembly
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
US4863343A (en) * 1988-05-16 1989-09-05 Westinghouse Electric Corp. Turbine vane shroud sealing system
WO1991007572A1 (en) * 1989-11-20 1991-05-30 Allied-Signal Inc. High temperature turbine engine structure
US5074752A (en) * 1990-08-06 1991-12-24 General Electric Company Gas turbine outlet guide vane mounting assembly
US5228284A (en) * 1988-12-06 1993-07-20 Allied-Signal Inc. High temperature turbine engine structure
GB2267541A (en) * 1992-06-04 1993-12-08 Rolls Royce Plc Mounting gas turbine outlet guide vanes
US5269651A (en) * 1990-06-02 1993-12-14 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Guide vane ring of a turbine of a gas turbine engine
US5279031A (en) * 1988-12-06 1994-01-18 Alliedsignal Inc. High temperature turbine engine structure
US5290143A (en) * 1992-11-02 1994-03-01 Allied Signal Bicast vane and shroud rings
US5411368A (en) * 1993-11-08 1995-05-02 Allied-Signal Inc. Ceramic-to-metal stator vane assembly with braze
US5584652A (en) * 1995-01-06 1996-12-17 Solar Turbines Incorporated Ceramic turbine nozzle
US20090155068A1 (en) * 2007-12-13 2009-06-18 Eric Durocher Radial loading element for turbine vane
US20100071208A1 (en) * 2008-09-23 2010-03-25 Eric Durocher Guide tool and method for assembling radially loaded vane assembly of gas turbine engine
US7934900B1 (en) * 1977-08-03 2011-05-03 Rolls-Royce Limited Nozzle guide vane for a gas turbine engine
RU2448258C2 (ru) * 2006-01-03 2012-04-20 Дженерал Электрик Компани Сборка турбинной лопатки для газотурбинного двигателя и газотурбинный статор, включающий данную сборку
US20130014512A1 (en) * 2011-07-13 2013-01-17 United Technologies Corporation Ceramic Matrix Composite Combustor Vane Ring Assembly
US20130089417A1 (en) * 2011-10-07 2013-04-11 David J. Wiebe Wear prevention system for securing compressor airfoils within a turbine engine
EP3009608A1 (en) * 2014-10-02 2016-04-20 United Technologies Corporation Vane assembly with trapped segmented vane structures
US10132186B2 (en) 2015-08-13 2018-11-20 General Electric Company System and method for supporting a turbine shroud
US11286798B2 (en) * 2019-08-20 2022-03-29 Rolls-Royce Corporation Airfoil assembly with ceramic matrix composite parts and load-transfer features
EP4086436A1 (en) * 2021-05-04 2022-11-09 Raytheon Technologies Corporation Gas turbine vane assembly
US12071864B2 (en) 2022-01-21 2024-08-27 Rtx Corporation Turbine section with ceramic support rings and ceramic vane arc segments

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4053257A (en) * 1976-02-20 1977-10-11 Westinghouse Electric Corporation Stator vane assembly for gas turbines
US4245954A (en) * 1978-12-01 1981-01-20 Westinghouse Electric Corp. Ceramic turbine stator vane and shroud support
US4907946A (en) * 1988-08-10 1990-03-13 General Electric Company Resiliently mounted outlet guide vane

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE826673C (de) * 1945-04-04 1952-01-03 Maschf Augsburg Nuernberg Ag Leitapparat mit keramischen Leitschaufeln
FR57426E (fr) * 1946-01-11 1953-01-28 Perfectionnements aux turbines à gaz
US2801076A (en) * 1952-11-18 1957-07-30 Parsons & Marine Eng Turbine Turbine nozzles
US3025037A (en) * 1957-10-24 1962-03-13 Bert F Beckstrom Gas turbine
DE1136350B (de) * 1959-08-11 1962-09-13 Entwicklungsbau Pirna Veb Verstellvorrichtung fuer Leitschaufelkraenze einer Axial-Stroemungsmaschine
US3619077A (en) * 1966-09-30 1971-11-09 Gen Electric High-temperature airfoil
US3719427A (en) * 1971-03-22 1973-03-06 Caterpillar Tractor Co Variable area nozzle for turbines or compressors

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE826673C (de) * 1945-04-04 1952-01-03 Maschf Augsburg Nuernberg Ag Leitapparat mit keramischen Leitschaufeln
FR57426E (fr) * 1946-01-11 1953-01-28 Perfectionnements aux turbines à gaz
US2801076A (en) * 1952-11-18 1957-07-30 Parsons & Marine Eng Turbine Turbine nozzles
US3025037A (en) * 1957-10-24 1962-03-13 Bert F Beckstrom Gas turbine
DE1136350B (de) * 1959-08-11 1962-09-13 Entwicklungsbau Pirna Veb Verstellvorrichtung fuer Leitschaufelkraenze einer Axial-Stroemungsmaschine
US3619077A (en) * 1966-09-30 1971-11-09 Gen Electric High-temperature airfoil
US3719427A (en) * 1971-03-22 1973-03-06 Caterpillar Tractor Co Variable area nozzle for turbines or compressors

Cited By (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3966353A (en) * 1975-02-21 1976-06-29 Westinghouse Electric Corporation Ceramic-to-metal (or ceramic) cushion/seal for use with three piece ceramic stationary vane assembly
JPS51108110A (nl) * 1975-02-21 1976-09-25 Westinghouse Electric Corp
JPS561445B2 (nl) * 1975-02-21 1981-01-13
USB552006I5 (nl) * 1975-02-24 1976-02-03
USB563412I5 (nl) * 1975-03-28 1976-02-24
US3992127A (en) * 1975-03-28 1976-11-16 Westinghouse Electric Corporation Stator vane assembly for gas turbines
US4076451A (en) * 1976-03-05 1978-02-28 United Technologies Corporation Ceramic turbine stator
US4008978A (en) * 1976-03-19 1977-02-22 General Motors Corporation Ceramic turbine structures
US7934900B1 (en) * 1977-08-03 2011-05-03 Rolls-Royce Limited Nozzle guide vane for a gas turbine engine
US4180371A (en) * 1978-03-22 1979-12-25 Avco Corporation Composite metal-ceramic turbine nozzle
US4552509A (en) * 1980-01-31 1985-11-12 Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for joining two relatively rotatable turbomachine components
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
US4768924A (en) * 1986-07-22 1988-09-06 Pratt & Whitney Canada Inc. Ceramic stator vane assembly
US4863343A (en) * 1988-05-16 1989-09-05 Westinghouse Electric Corp. Turbine vane shroud sealing system
US5116158A (en) * 1988-12-06 1992-05-26 Allied-Signal Inc. High temperature turbine engine structure
US5228284A (en) * 1988-12-06 1993-07-20 Allied-Signal Inc. High temperature turbine engine structure
US5279031A (en) * 1988-12-06 1994-01-18 Alliedsignal Inc. High temperature turbine engine structure
WO1991007572A1 (en) * 1989-11-20 1991-05-30 Allied-Signal Inc. High temperature turbine engine structure
US5269651A (en) * 1990-06-02 1993-12-14 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Guide vane ring of a turbine of a gas turbine engine
US5074752A (en) * 1990-08-06 1991-12-24 General Electric Company Gas turbine outlet guide vane mounting assembly
GB2267541A (en) * 1992-06-04 1993-12-08 Rolls Royce Plc Mounting gas turbine outlet guide vanes
US5306118A (en) * 1992-06-04 1994-04-26 Rolls-Royce Plc Mounting gas turbine outlet guide vanes
GB2267541B (en) * 1992-06-04 1995-08-09 Rolls Royce Plc Mounting gas turbine outlet guide vanes
US5290143A (en) * 1992-11-02 1994-03-01 Allied Signal Bicast vane and shroud rings
US5411368A (en) * 1993-11-08 1995-05-02 Allied-Signal Inc. Ceramic-to-metal stator vane assembly with braze
US5584652A (en) * 1995-01-06 1996-12-17 Solar Turbines Incorporated Ceramic turbine nozzle
RU2448258C2 (ru) * 2006-01-03 2012-04-20 Дженерал Электрик Компани Сборка турбинной лопатки для газотурбинного двигателя и газотурбинный статор, включающий данную сборку
US20090155068A1 (en) * 2007-12-13 2009-06-18 Eric Durocher Radial loading element for turbine vane
US8096746B2 (en) 2007-12-13 2012-01-17 Pratt & Whitney Canada Corp. Radial loading element for turbine vane
US8453326B2 (en) 2008-09-23 2013-06-04 Pratt & Whitney Canada Corp. Method for assembling radially loaded vane assembly of gas turbine engine
US20100071208A1 (en) * 2008-09-23 2010-03-25 Eric Durocher Guide tool and method for assembling radially loaded vane assembly of gas turbine engine
US8151422B2 (en) 2008-09-23 2012-04-10 Pratt & Whitney Canada Corp. Guide tool and method for assembling radially loaded vane assembly of gas turbine engine
US9335051B2 (en) * 2011-07-13 2016-05-10 United Technologies Corporation Ceramic matrix composite combustor vane ring assembly
US20130014512A1 (en) * 2011-07-13 2013-01-17 United Technologies Corporation Ceramic Matrix Composite Combustor Vane Ring Assembly
US20130089417A1 (en) * 2011-10-07 2013-04-11 David J. Wiebe Wear prevention system for securing compressor airfoils within a turbine engine
US8920116B2 (en) * 2011-10-07 2014-12-30 Siemens Energy, Inc. Wear prevention system for securing compressor airfoils within a turbine engine
EP3009608A1 (en) * 2014-10-02 2016-04-20 United Technologies Corporation Vane assembly with trapped segmented vane structures
US20160201488A1 (en) * 2014-10-02 2016-07-14 United Technologies Corporation Vane assembly with trapped segmented vane structures
US10392951B2 (en) 2014-10-02 2019-08-27 United Technologies Corporation Vane assembly with trapped segmented vane structures
US10132186B2 (en) 2015-08-13 2018-11-20 General Electric Company System and method for supporting a turbine shroud
US11286798B2 (en) * 2019-08-20 2022-03-29 Rolls-Royce Corporation Airfoil assembly with ceramic matrix composite parts and load-transfer features
EP4086436A1 (en) * 2021-05-04 2022-11-09 Raytheon Technologies Corporation Gas turbine vane assembly
US11512604B1 (en) 2021-05-04 2022-11-29 Raytheon Technologies Corporation Spring for radially stacked assemblies
US12071864B2 (en) 2022-01-21 2024-08-27 Rtx Corporation Turbine section with ceramic support rings and ceramic vane arc segments

Also Published As

Publication number Publication date
DE2437486A1 (de) 1975-02-20
JPS5044309A (nl) 1975-04-21
SE7410246L (nl) 1975-02-10
NL7409924A (nl) 1975-02-11
FR2240355B1 (nl) 1980-03-21
DE2437486C2 (de) 1983-08-18
SE392147B (sv) 1977-03-14
CA995141A (en) 1976-08-17
FR2240355A1 (nl) 1975-03-07
JPS5228168B2 (nl) 1977-07-25
CH585845A5 (nl) 1977-03-15
IT1017716B (it) 1977-08-10
GB1470989A (en) 1977-04-21

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