US3892497A - Axial flow turbine stationary blade and blade ring locking arrangement - Google Patents

Axial flow turbine stationary blade and blade ring locking arrangement Download PDF

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Publication number
US3892497A
US3892497A US469928A US46992874A US3892497A US 3892497 A US3892497 A US 3892497A US 469928 A US469928 A US 469928A US 46992874 A US46992874 A US 46992874A US 3892497 A US3892497 A US 3892497A
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United States
Prior art keywords
inner casing
arcuate
segments
arcuate support
axial flow
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
US469928A
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English (en)
Inventor
Richard P Gunderlock
Ted H Knutzen
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CBS Corp
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Westinghouse Electric Corp
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Filing date
Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Priority to US469928A priority Critical patent/US3892497A/en
Priority to CA223,946A priority patent/CA1015665A/en
Priority to JP5479475A priority patent/JPS5330847B2/ja
Priority to GB2010275A priority patent/GB1476553A/en
Priority to IT23262/75A priority patent/IT1038116B/it
Priority to FR7515041A priority patent/FR2271400B3/fr
Application granted granted Critical
Publication of US3892497A publication Critical patent/US3892497A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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

Definitions

  • An axial flow gas turbine has inner and outer casings. Arrays of stationary integral vane segments and adja- [52] U.S.Cl. 415/134, 3115501137855.441155912319; cent arcuate blade ring segments are Supported 51 l Cl Fold 25 24 wardly from and interlocked with the inner casing by l l i 134 arcuate segmented support members.
  • the arcuate [5 1 le 0 care g/ support members are fixedly attached to the inner casing by an arrangement of interlocking plates and bolts in registration with said support members.
  • This invention relates generally to gas turbines. and more specifically to shroud and blade ring support arrangements within a gas turbine engine.
  • Turbines operated with hot motive gases for example gas turbines. require cooling fluid such as air. to control temperatures of stationary components as well as rotating components.
  • Turbines of this type are usually provided with outer casings divided in a horizontal plane with an upper and lower half bolted together for easy assembly and service. Also. pressurized cooling air or other suitable fluid is directed through the outer casing into an outer plenum chamber or space between the outer casing and the outer diaphragm shrouds and then through the stationary turbine blades. It has been found that undesirable leakage of cooling air from the plenum chamber into the motive fluid flow path occurs during machine operation.
  • an excitation pattern can still persist as a result of changes in stationary blade gauging or pitch, i.e.. spacing between adjacent blades through which the motive fluid flows.
  • Changes in gauging results when the outer shrouds of the stationary blade diaphragm expand relative to the casing with consequent uneven shifting of the stationary blades in the circumferential direction.
  • the amount of gauging change is proportional to the number of blades in the integral structure which is maximum for a two-half diaphragm system.
  • shroud restraints in existing l80 divided diaphragms can develop excessive thermal stresses of a damaging nature during transient operating temperature cycles.
  • an axial flow gas turbine having a split casing.
  • the split casing comprises an outer casing and an inner casing with a plenum chamber therebetween.
  • the inner casing permits arcuate support members to be disposed inwardly thereof and adjacent thereto.
  • the arcuate support members in turn provide support for vane seg ments and blade rings.
  • Each arcuate support segment supporting a vane segment is locked to the inner casing by a bolt arrangement.
  • the arcuate support segments adjacent the horizontal split in the casings are secured with a locking plate that provides restrain against movement of the arcuate support segments in both circumferential directions.
  • Each arcuate support segment supporting the downstream edge of each blade ring has a generally radially directed lock plate restraining both the arcuate support segment and its respective blade ring.
  • FIG. I is an axial sectional view of a portion of a gas turbine engine incorporating the invention.
  • FIG. 2 is an axial sectional view of the locking arrangement for the arcuate support segments constructed in accordance with the principles of this invention
  • FIG. 3 is a view taken along the lines III-III of FIG. 2;
  • FIG. 4 is a transverse view of a portion of an annular array of ring segments and locking plates
  • FIG. 5 is a prior art view of the locking arrangement of segments adjacent the horizontal split in the turbine casing
  • FIG. 6 is another view of the prior art taken along the lines VIVI of FIG. 5;
  • FIG. 7 is an axial sectional view of a prior art locking arrangement
  • FIG. 8 is a view of the locking arrangement of arcuate support segments adjacent the horizontal split in the casing. constructed in accordance with the principles of this invention.
  • FIG. 9 is a view taken along the lines lXlX of FIG. 8, showing both the upper and lower casing halves.
  • FIG. 1 there is shown an axial flow gas turbine 10. Only a portion of the upper half is shown since the lower half is identical to the upper half.
  • the turbine I0 comprises an outer casing 12 of generally tubular or annular shape. a plurality of inner casing members 14 of annular shape encompassed by the outer casing I2, and a rotor 16 rotatably supported within each of the inner casing members 14, in any suitable manner. not shown.
  • Cooperatively associated with the rotor blades 18 and 20. to form two stages. for this example. for motive fluid expansion. is an equal number of blade diaphragms or annular rows of stationary blades 22 and 24, supported within the inner casing members 14.
  • An annular grouping of stationary blades 22 or 24. comprises an integral arcuate vane segment 23.
  • the rotor blades 18 are substantially similar to each other except for a gradual increase in height from left to right. and are of the unshrouded type with a radially outwardly extending vane portion 26 and a root portion 28 suitably secured to the rotor 16.
  • the stationary blades 22 and 24 are substantially similar to each other but gradually increase in height from left to right. and are provided with a radially inwardly extending vane portion 30, a base portion 32. and an outer shroud portion 34.
  • the outer shroud portion 34 comprises a portion of the track and channel arrangement 49 for supporting the integral vane segments 23.
  • hot motive fluid such as pressurized combustion gas. generated in a suitable combustion chamber. not shown. is directed through the first row of stationary vanes 22 past the rotor blades 18 and 20. in the direction indicated by the arrow 35a. with the resulting expansion of the hot motive fluid to rotate the rotor 16 about its longitudinal axis. and thence directed through a suitable outlet. not shown. located at the furthermost downstream end of the turbine 10.
  • the arcuate support or isolation segments 44 provide the support for the outer shroud portions 34 of the stationary arcuate vane segments 23 that comprise the annular arrays of stationary blades 22 and 24. and the blade rings 46.
  • the arcuate support seg ments 44 slid-ably mate with grooves 45 in each inner casing member 14 in a track and channel arrangement 51 to support the stationary vane segments 23 comprised of the blades 22 and 24.
  • the arcuate support segments 44 help support axially adjacent arcuate blade ring segments 46.
  • the number of stationary vane segments 23 and the arcuate blade ring segments 46 control the number of gaps or open ings between circumferentially adjacent shroud portions 34 and between circumferentially adjacent arcuate blade ring segments 46. This aids in controlling the leakage of cooling air therepast.
  • the arcuate ring segments 46 have a gap 76 between one another as shown in FIG. 4.
  • the arcuate support segments 44 and the vane segments 23 do likewise.
  • Disposed across the gap 76 between circumferentially adjacent arcuate ring segments 46 is a plate-like seal member 78.
  • the seal member 78 is fixedly attached to one ring segment 46.
  • Each arcuate isolation or support segment 44 is restrained however. with respect to the inner casing 14, as shown in FIGS. 1 and 2.
  • the restraint is at a single point on its radially outer periphery of each arcuate support segment 44 to permit expansion and contraction with minimum deleterious effects therein.
  • the furthermost upstream arcuate support segment 44 per inner casing member 14 as shown in FIG. 2. is designated 44a. It has a track and channel interlock arrangement 51 with the upstream end of its respective inner casing member 14.
  • the upstream and downstream ends of each inner casing member 14 have radially directed flanges 82 and 84, respectively.
  • the upstream and downstream flanges. 82 and 84 permit the support arrangements. not shown. and annular seal arrangement 43.
  • Each upstream arcuate support member 44a is restrained from circumferential movement or slippage by a radially directed lock plate 53.
  • Each radially directed lock plate 53 is anchored to inner casing 14 by a bolt 53'. The radially directed lock plate 53 mates with a radially directed groove 86 in a lip member 87 on its arcuate support member 44a.
  • a support arrangement is shown in the furthermost downstream arcuate support segment 440 on inner casing member 14 which has a similar track and channel interlock arrangement 51 for support therewith.
  • a radially directed lock plate 50 has a similar bolt 50' holding the plate 50 to the downstream side of the inner casing member 14.
  • the lock plate 50 is seated in a radially directed groove 55 on the downstream side of the inner casing 14.
  • the lock plate 50 extends radially inwardly and mates with a groove 57 in lip member 58 in the downstream side of arcuate support segment 44c.
  • the lock plate 50 extends further inwardly and mates with a notch 56 disposed on the downstream lip of its respective arcuate bladering segment 46. as shown in H68. 2 and 3.
  • arcuate support segment 44b Disposed intermediate between the upstream and downstream arcuate support segments 44a and 440. is an annular array of arcuate support segments 44b. supported by the inner casing member l4 by a track and channel interlock arrangement 51. Each intermediately disposed arcuate segment 44b is restrained from circumferential dislocation by a bolt 48 disposed through the inner casing member l4 and being in registration with said arcuate support segment 4411.
  • FIG. 6 shows both halves of the prior art split turbine casing designated C and D respectively. This arrangement only prevented dislocation of arcuate isolation segments 44 in one direction.
  • the improvement is shown in FIGS. 8 and 9, wherein a horizontal joint locking plate 59 has a tang portion 60 mated into a groove 61 ofa lip member 62 on support segment 44. The locking plate 59 is held to each arcuate support segment 44 adjacent the horizontal split in the casings l4 and 12 by a bolt 63 in casing 14.
  • FIG. 9 shows both the upper and lower portions of the turbine casing, designated A and B respectively.
  • An axial flow turbomachine comprising:
  • a rotor having an array of rotatable blades on its periphery. said rotatable blades being mounted coaxial and adjacent said stationary blades;
  • said array of stationary blades comprising arcuate integral vane segments thereof;
  • said stationary blades being supported from said inner casing by arcuate support segments disposed on the upstream portions and intermediate portions, of said inner casing. all of said arcuate support segments and said innner casing having a track and channel interlock means therebetween, said arcuate support segments and said outer shroud portion of said stationary integral vane segments and said blade rings having a track and channel interlock means therebetween. the downstream edge of said blade rings supported by an array of arcuate support segments. each arcuate support segment having means to fixedly attach at least one point of its radially outer periphery to the inner casing to permit free circumferential expansion and contraction of said arcuate support segments;
  • said inner and outer casings being separable longitudinal into generally upper and lower halves;
  • each semi-annular array having one of said arcuate support segments at each respective end thereof, said arcuate support segments at each end of each semi-annular array being fixedly at tached to said inner casing by a locking plate.
  • each of said arcuate support segments supporting said arcuate blade ring segments are interlocked with said inner casing by a generally radially directed locking member.
  • each of said generally radially directed locking members interlocking said inner casing and each respective arcuate blade ring segment, is fixedly attached to said inner casing.
  • each of said generally radially directed locking members extending radially inwardly to and mating with a generally radially directed channel in each of said arcuate support segments and a notch in each of said blade rings to prevent dislocation therewith.
  • each of said locking plates is bolted to one of said inner casing halves.
  • a tang member on said locking plate being disposed in a groove on a lip portion on said arcuate support segment to inter lock with and prevent circumferential motion thereof.
  • each of said locking plates being secured to an inner casing halve by a bolt.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US469928A 1974-05-14 1974-05-14 Axial flow turbine stationary blade and blade ring locking arrangement Expired - Lifetime US3892497A (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US469928A US3892497A (en) 1974-05-14 1974-05-14 Axial flow turbine stationary blade and blade ring locking arrangement
CA223,946A CA1015665A (en) 1974-05-14 1975-04-07 Axial flow turbine stationary blade and blade ring locking arrangement
JP5479475A JPS5330847B2 (it) 1974-05-14 1975-05-12
GB2010275A GB1476553A (en) 1974-05-14 1975-05-13 Gas turbine
IT23262/75A IT1038116B (it) 1974-05-14 1975-05-13 Complesso delle palette fisse per turbina a flusso assiale e complesso di bloccaggio degli anelli portapalette
FR7515041A FR2271400B3 (it) 1974-05-14 1975-05-14

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US469928A US3892497A (en) 1974-05-14 1974-05-14 Axial flow turbine stationary blade and blade ring locking arrangement

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US3892497A true US3892497A (en) 1975-07-01

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US469928A Expired - Lifetime US3892497A (en) 1974-05-14 1974-05-14 Axial flow turbine stationary blade and blade ring locking arrangement

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US (1) US3892497A (it)
JP (1) JPS5330847B2 (it)
CA (1) CA1015665A (it)
FR (1) FR2271400B3 (it)
GB (1) GB1476553A (it)
IT (1) IT1038116B (it)

Cited By (53)

* Cited by examiner, † Cited by third party
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US3975114A (en) * 1975-09-23 1976-08-17 Westinghouse Electric Corporation Seal arrangement for turbine diaphragms and the like
US3975112A (en) * 1975-06-09 1976-08-17 United Technologies Corporation Apparatus for sealing a gas turbine flow path
US3981609A (en) * 1975-06-02 1976-09-21 United Technologies Corporation Coolable blade tip shroud
US4101242A (en) * 1975-06-20 1978-07-18 Rolls-Royce Limited Matching thermal expansion of components of turbo-machines
US4171614A (en) * 1976-04-17 1979-10-23 Motoren- Und Turbinen-Union Munchen Gmbh Gas turbine engine
US4247248A (en) * 1978-12-20 1981-01-27 United Technologies Corporation Outer air seal support structure for gas turbine engine
US4355952A (en) * 1979-06-29 1982-10-26 Westinghouse Electric Corp. Combustion turbine vane assembly
US4439982A (en) * 1979-02-28 1984-04-03 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for maintaining clearances between a turbine rotor and casing
US4492517A (en) * 1983-01-06 1985-01-08 General Electric Company Segmented inlet nozzle for gas turbine, and methods of installation
FR2552812A1 (fr) * 1983-10-03 1985-04-05 Nuovo Pignone Spa Systeme pour fixer des tuyeres de stator a une enveloppe de turbine de puissance
US4537024A (en) * 1979-04-23 1985-08-27 Solar Turbines, Incorporated Turbine engines
US4630994A (en) * 1983-09-16 1986-12-23 Motoren-Und Turbinen Union Munchen Gmbh Apparatus for axially and circumferentially locking stationary casing components of turbomachines
US4688988A (en) * 1984-12-17 1987-08-25 United Technologies Corporation Coolable stator assembly for a gas turbine engine
US4728257A (en) * 1986-06-18 1988-03-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal stress minimized, two component, turbine shroud seal
US4749333A (en) * 1986-05-12 1988-06-07 The United States Of America As Represented By The Secretary Of The Air Force Vane platform sealing and retention means
US4762462A (en) * 1986-11-26 1988-08-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Housing for an axial compressor
US4787817A (en) * 1985-02-13 1988-11-29 Societe Nationale D'etude Et De Construction De Moteurs D-Aviation (Snecma) Device for monitoring clearance between rotor blades and a housing
FR2617538A1 (fr) * 1987-07-01 1989-01-06 Rolls Royce Plc Structure de carenage d'aubes de turbine
US4816213A (en) * 1987-08-24 1989-03-28 Westinghouse Electric Corp. Thermal distortion isolation system for turbine blade rings
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
US4920742A (en) * 1988-05-31 1990-05-01 General Electric Company Heat shield for gas turbine engine frame
US4957412A (en) * 1988-09-06 1990-09-18 Westinghouse Electric Corp. Apparatus and method for supporting the torque load on a gas turbine vane
US5127797A (en) * 1990-09-12 1992-07-07 United Technologies Corporation Compressor case attachment means
US5145316A (en) * 1989-12-08 1992-09-08 Rolls-Royce Plc Gas turbine engine blade shroud assembly
US5158430A (en) * 1990-09-12 1992-10-27 United Technologies Corporation Segmented stator vane seal
US5224824A (en) * 1990-09-12 1993-07-06 United Technologies Corporation Compressor case construction
US5320486A (en) * 1993-01-21 1994-06-14 General Electric Company Apparatus for positioning compressor liner segments
US5387082A (en) * 1992-10-05 1995-02-07 Asea Brown Boveri Ltd. Guide wave suspension for an axial-flow turbomachine
US5412939A (en) * 1993-12-20 1995-05-09 Alliedsignal Inc. Seal compression tool for gas turbine engine
US5503490A (en) * 1994-05-13 1996-04-02 United Technologies Corporation Thermal load relief ring for engine case
US5564897A (en) * 1992-04-01 1996-10-15 Abb Stal Ab Axial turbo-machine assembly with multiple guide vane ring sectors and a method of mounting thereof
US5618161A (en) * 1995-10-17 1997-04-08 Westinghouse Electric Corporation Apparatus for restraining motion of a turbo-machine stationary vane
WO2000057033A1 (de) 1999-03-24 2000-09-28 Siemens Aktiengesellschaft Abdeckelement und anordnung mit einem abdeckelement und mit einer tragstruktur
US6217279B1 (en) * 1997-06-19 2001-04-17 Mitsubishi Heavy Industries, Ltd. Device for sealing gas turbine stator blades
EP1106784A2 (en) * 1999-12-07 2001-06-13 General Electric Company Turbine stator vane frame
FR2829525A1 (fr) * 2001-09-13 2003-03-14 Snecma Moteurs Assemblage de secteurs d'un distributeur de turbine a un carter
US6533542B2 (en) * 2001-01-15 2003-03-18 Mitsubishi Heavy Industries, Ltd. Split ring for gas turbine casing
US20070237630A1 (en) * 2006-04-11 2007-10-11 Siemens Power Generation, Inc. Vane shroud through-flow platform cover
US20080050225A1 (en) * 2005-03-24 2008-02-28 Alstom Technology Ltd Heat accumulation segment
US20080050224A1 (en) * 2005-03-24 2008-02-28 Alstom Technology Ltd Heat accumulation segment
US20110097201A1 (en) * 2009-10-28 2011-04-28 Alstom Technology Ltd Steam turbine casing system
US20120045312A1 (en) * 2010-08-20 2012-02-23 Kimmel Keith D Vane carrier assembly
JP2013256945A (ja) * 2012-06-11 2013-12-26 General Electric Co <Ge> タービンの真円からのずれの影響を緩和する方法及び装置
DE102014202746A1 (de) * 2014-02-14 2015-08-20 Siemens Aktiengesellschaft Eingegossener Stahlring in Eisengussgehäuse für Dampfturbinen
US9188062B2 (en) 2012-08-30 2015-11-17 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine
US20150369409A1 (en) * 2013-03-15 2015-12-24 United Technologies Corporation Low leakage duct segment using expansion joint assembly
US9435226B2 (en) 2011-06-20 2016-09-06 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine and repairing method of gas turbine
US20170268367A1 (en) * 2016-03-16 2017-09-21 United Technologies Corporation Seal anti-rotation feature
US20180149042A1 (en) * 2016-11-30 2018-05-31 Rolls-Royce Corporation Turbine Shroud Assembly with Locating Pads
US20180149030A1 (en) * 2016-11-30 2018-05-31 Rolls-Royce Corporation Turbine shroud with hanger attachment
CN109113798A (zh) * 2018-08-27 2019-01-01 广东惠州天然气发电有限公司 一种新型燃气轮机静叶环
US11111796B1 (en) * 2020-05-18 2021-09-07 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with dovetail retention system
US11434785B2 (en) * 2018-06-28 2022-09-06 MTU Aero Engines AG Jacket ring assembly for a turbomachine

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US7094029B2 (en) * 2003-05-06 2006-08-22 General Electric Company Methods and apparatus for controlling gas turbine engine rotor tip clearances
JP4648139B2 (ja) * 2005-09-14 2011-03-09 三菱重工業株式会社 ガスタービンの翼端隙間管理構造
JP5461636B2 (ja) * 2012-08-24 2014-04-02 三菱重工業株式会社 タービン分割環

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Cited By (72)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3981609A (en) * 1975-06-02 1976-09-21 United Technologies Corporation Coolable blade tip shroud
US3975112A (en) * 1975-06-09 1976-08-17 United Technologies Corporation Apparatus for sealing a gas turbine flow path
US4101242A (en) * 1975-06-20 1978-07-18 Rolls-Royce Limited Matching thermal expansion of components of turbo-machines
US3975114A (en) * 1975-09-23 1976-08-17 Westinghouse Electric Corporation Seal arrangement for turbine diaphragms and the like
US4171614A (en) * 1976-04-17 1979-10-23 Motoren- Und Turbinen-Union Munchen Gmbh Gas turbine engine
US4247248A (en) * 1978-12-20 1981-01-27 United Technologies Corporation Outer air seal support structure for gas turbine engine
US4439982A (en) * 1979-02-28 1984-04-03 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for maintaining clearances between a turbine rotor and casing
US4537024A (en) * 1979-04-23 1985-08-27 Solar Turbines, Incorporated Turbine engines
US4355952A (en) * 1979-06-29 1982-10-26 Westinghouse Electric Corp. Combustion turbine vane assembly
US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
US4492517A (en) * 1983-01-06 1985-01-08 General Electric Company Segmented inlet nozzle for gas turbine, and methods of installation
US4630994A (en) * 1983-09-16 1986-12-23 Motoren-Und Turbinen Union Munchen Gmbh Apparatus for axially and circumferentially locking stationary casing components of turbomachines
FR2552812A1 (fr) * 1983-10-03 1985-04-05 Nuovo Pignone Spa Systeme pour fixer des tuyeres de stator a une enveloppe de turbine de puissance
US4688988A (en) * 1984-12-17 1987-08-25 United Technologies Corporation Coolable stator assembly for a gas turbine engine
US4787817A (en) * 1985-02-13 1988-11-29 Societe Nationale D'etude Et De Construction De Moteurs D-Aviation (Snecma) Device for monitoring clearance between rotor blades and a housing
US4749333A (en) * 1986-05-12 1988-06-07 The United States Of America As Represented By The Secretary Of The Air Force Vane platform sealing and retention means
US4728257A (en) * 1986-06-18 1988-03-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal stress minimized, two component, turbine shroud seal
US4762462A (en) * 1986-11-26 1988-08-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Housing for an axial compressor
US4863345A (en) * 1987-07-01 1989-09-05 Rolls-Royce Plc Turbine blade shroud structure
FR2617538A1 (fr) * 1987-07-01 1989-01-06 Rolls Royce Plc Structure de carenage d'aubes de turbine
US4816213A (en) * 1987-08-24 1989-03-28 Westinghouse Electric Corp. Thermal distortion isolation system for turbine blade rings
US4920742A (en) * 1988-05-31 1990-05-01 General Electric Company Heat shield for gas turbine engine frame
US4957412A (en) * 1988-09-06 1990-09-18 Westinghouse Electric Corp. Apparatus and method for supporting the torque load on a gas turbine vane
US5145316A (en) * 1989-12-08 1992-09-08 Rolls-Royce Plc Gas turbine engine blade shroud assembly
US5127797A (en) * 1990-09-12 1992-07-07 United Technologies Corporation Compressor case attachment means
US5158430A (en) * 1990-09-12 1992-10-27 United Technologies Corporation Segmented stator vane seal
US5224824A (en) * 1990-09-12 1993-07-06 United Technologies Corporation Compressor case construction
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Also Published As

Publication number Publication date
JPS50155819A (it) 1975-12-16
FR2271400A1 (it) 1975-12-12
CA1015665A (en) 1977-08-16
GB1476553A (en) 1977-06-16
FR2271400B3 (it) 1978-11-17
JPS5330847B2 (it) 1978-08-30
IT1038116B (it) 1979-11-20

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