US3841787A - Axial flow turbine structure - Google Patents

Axial flow turbine structure Download PDF

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Publication number
US3841787A
US3841787A US00394599A US39459973A US3841787A US 3841787 A US3841787 A US 3841787A US 00394599 A US00394599 A US 00394599A US 39459973 A US39459973 A US 39459973A US 3841787 A US3841787 A US 3841787A
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US
United States
Prior art keywords
segments
inner casing
arcuate
stationary
casing
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
US00394599A
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English (en)
Inventor
A Scalzo
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.)
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 US00394599A priority Critical patent/US3841787A/en
Priority to CA206,953A priority patent/CA975300A/en
Priority to NL7410982A priority patent/NL7410982A/nl
Priority to DE2439339A priority patent/DE2439339C2/de
Priority to CH1128174A priority patent/CH583850A5/xx
Priority to GB3733274A priority patent/GB1461965A/en
Priority to IT26782/74A priority patent/IT1020335B/it
Priority to JP10000474A priority patent/JPS5337484B2/ja
Priority to SE7411255A priority patent/SE392151B/xx
Priority to FR7430188A priority patent/FR2242565B1/fr
Application granted granted Critical
Publication of US3841787A publication Critical patent/US3841787A/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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • Arrays of stationary integral vane segments and adjacent arcuate blade ring segments are supported inwardly from and interlocked with the inner casing by arcuate segmented support members.
  • the arcuate segmented support members are each fixedly attached at their centermost point to the inner casing. This arrangement permits thermal expansion between mating members with respect to each other.
  • individually locked stationary integral vane segments and arcuate blade ring segments provide an arrangement where blade path leakage harmonics are limited to the number of such segments in each of their respective planes across the turbine, thus eliminating the deleterious effects created by even harmonics of two stationary half blade segment structures.
  • Turbines operated with hot motive gases require cooling fluids, 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 upper and lower halves bolted together, for ease of assembly and service.
  • pressurized cooling air or other suitable fluid is directed through the outer easing into the annular plenum chamber or space between the outer casings and the outer diaphragm shrouds and then through the stationary turbine blades. It has been found that undesirable leakage of cooling air from the annular space into the motive fluid flow path occurs in 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 diaphragms expand relative to the casing with consequent uneven shifting in circumferential direction of the stationary blades.
  • 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 180 divided diaphragms can develop excessive thermal stresses of a damaging nature during transient operating temperature cycles.
  • One of the primary objects of this invention is to provide a turbine structure having inner and outer casings in which damaging leakage of cooling air between adjacent stationary blade shroud segments is eliminated.
  • a further object of this invention is to provide an improved turbine structure in which the inner casing is freely supported-in a horizontal relationship with respect to the outer casing.
  • a still further object of the invention is to provide an improved turbine structure in which the inner casing is maintained in vertical alignment with respect to the outer casing.
  • Yet another object of the invention is to provide an improved stationary blade diaphragm and inner casing structure for a turbine wherein the blades are formed in a manner to conduct cooling air flow, wherein leakage of cooling air therepast is minimized, and in which the blades are free to expand relative to their support ing members and to the casing.
  • a still further object of the invention is to provide an improved mounting arrangement for an annular row of hollow air cooled stationary blade segments and axially adjacent blade ring segments.
  • an axial flow gas turbine having an annular row of stationary blades, an annular row of rotatable blades carried by a rotor and cooperatively associated with the stationary blades, and an annular multiple member inner casing emcompassing the stationary blades and the rotatable blades.
  • annular outer casing encompassing the inner casing and jointly therewith providing a common plenum chamber or space of annular shape.
  • the inner casing is supported and maintained horizontally within the outer casing by flange-like keys disposed between the two casings.
  • the keys extend horizontally outwardly off the inner casing wall and engage a key receiving member within the inner walls of the outer casing.
  • the inner casing is held in vertical alignment by a plurality of pins disposed in the longitudinally vertical plane between the two casings.
  • the inner casing engages arcuate support segment. These arcuate support segments and easing slidably mate because of track and channel interlock arrangements on the inner side of the inner casing and the support segments.
  • the radially inner edges of the arcuate supportsegments mate with the stationary vane segments and with the arcuate blade ring segments.
  • the arcuate support segments are locked or fixedly attached only at their midpoint, to the inner casing. This permits thermal expansion and also contraction within the support members with respect to the inner casing.
  • the slidable support arrangement also permits dimensional changes in the supported vane and arcuate blade ring segments with respect to one another.
  • FIG. I is an axial sectional view of a portion of a gas turbine incorporating the invention.
  • FIG. 2 is an axial sectional view of the locking arrangement for the support segments;
  • FIG. 3 is a view taken along the lines Ill-III of FIG.
  • FIG. 4 is a view of the locking arrangement for the stationary blade shroud segments.
  • FIG. 5 is a view taken along the lines V-V of FIG. 4.
  • 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 10 comprises an outer casing 12 of generally tubular or annular shape, multiple inner casings 14 of annular shape encompassed by the outer casing 12, and a rotor 16 rotatably supported within the multiple inner casings 14 in any suitable manner, not shown, and having a plurality, two in this example, of annular rows or arrays of blades 18 and 20.
  • An annular grouping of stationary blades 22 or 24, comprise an integral arcuate vane segment 23.
  • the rotor blades 18 and 20 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 for supporting the integral vane segments 23.
  • hot motive fluid such as pressurized combustion gas
  • a suitable combustion chamber not shown
  • hot motive fluid such as pressurized combustion gas
  • a suitable combustion chamber not shown
  • hot motive fluid 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 resulting expansion of the 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 inner casing 14 is supported within the outer casing 12 by keying members 36 disposed in the horizontal plane.
  • Each keying member 36 is slidably engaged with a keyway 38, or key member shoulder-like support.
  • the keying members 36 provide horizontal support for each member of the multiple inner casing 14.
  • FIG. 1 now in a vertical plane, there is shown a plurality of vertically disposed pins 40, which are located on the longitudinally vertical plane of the turbine 10.
  • the pins 40 are disposed on both the upper and the lower halves of the turbine 10.
  • the pins 40 transmit torque from the stationary blades, 22 and 24, only two shown, to the outer casing 12.
  • the vertically disposed pins 40 also maintain transverse alignment of each member of the multiple inner casing 14.
  • An annular plenum chamber 42 is disposed along the radially outward side of the multiple inner casing 14. Pressurized cooling air is introduced into the stationary blades 22 and 24, and the like, from the plenum chamber 42 through passageways, not shown, in the multiple inner casing 14.
  • a spring loaded arcuately segmented face seal 43 provides restriction of gas leakage between the motive fluid flow path and the plenum chamber 42.
  • Arcuate isolation segments 44 are disposed on the radially inner side of each member of the multiple inner casing 14.
  • the arcuate 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 like.
  • the arcuate isolation segments 44 slidably mate with grooves 45 in a track and channel arrangement 51 to support the stationary vane segments 23 comprised of the blades 22 and 24.
  • the isolation segments 44 also i tially adjacent arcuate blade ring segments 46. This controls leakage of cooling air therepast. Furthermore, the chances of undesirable even harmonics, which could damage the rotating blades 18 and 20, and the like, is eliminated.
  • the outer shroud members 34 and the arcuate blade ring segments 46 are slidably disposed on the radially inner edge of the arcuate isolation segments 44.
  • the upstream side of the arcuate blade ring segments 46 are slidably and supportively disposed in a track like shoulder and flange arrangement 47 with the downstream edge of adjacent upstream shroud members 34.
  • the slidable track and channel interlock and support arrangement 51 between the inner casing 14 and'the arcuate isolation segments 44 permit circumferential expansion of respective members in relation to one another, without buildup of stresses therein.
  • a similar track and channel interlock arrangement 49 is disposed between the arcuate isolation segments 44 and their respective supported members, which are the arcuate shroud members 34 and the arcuate blade ring segments 46.
  • the arcuate isolation segments 44 isolate the members of the multiple inner casing 14 from the hotter parts of the turbine, that is, the vane segments 23 and the arcuate blade ring segments 46, to prevent distortion within those members of the inner casing 14. Excessive distortion of the inner casing 14 would cause blade rubs and would reduce the performance of the turbine 10.
  • FIG. 2 shows an embodiment of a locking system for the arcuate isolation segments 44.
  • Retaining member 50 also locks the arcuate blade ring segments 46 with respect to each member of multiple inner casing 14, as shown in FIG. 3.
  • Contiguous surfaces of adjacent arcuate isolation segments 44, of adjacent shroud portions 34, and of adjacent arcuate blade ring segments 46, have male-female sealing strips 52 that provide a sealing arrangement between adjacent members. This reduces leakage of cooling air from the plenum chamber 42 into the hot motive fluid flow path.
  • the use of integral arcuate stationary vane segments 23 permits leakage harmonics that will not be dangerous to the turbine 10, if in fact any leakage does occur.
  • the vane segments 23 are locked with respect to the multiple inner casing 14 by an arrangement shown in FIGS. 4 and 5. Each vane segment 23 is fixedly attached from only a center point on its curvature to the inner casing 14. This reduces the deleterious effects of thermal expansion between mating members.
  • a vane segment lock pin 54 is disposed through each member of the multiple inner casing 14. The lock pin 54 is pro- .vided with machined flats 55 that registers with mating slots 60 in the radially outer portion of the shroud member 34. The pin 54 extends through a portion of the isolation segment 44 to register with each vane segment 23.
  • a lock pin retainer 56 maintains the lock pin 54 in registration with the member of the multiple inner casing14. The lock pin retainer 56 is secured to the member of the multiple inner casing 14 by bolts 57.
  • the flats 55 on the lock pin 54 extending into the slots 53 allows rotation of the lock pin 54 to orient the flats with the slots 60 to control contact stress.
  • An annular array of the individually locked vane segments 23 provide a unique leakage harmonic equal to the number of vane segments 23. This eliminates the troublesome family of even harmonics associated with the horizontal type joint leakage.
  • the male-female seal strips 52 between adjacent blade rings 46, between adjacent isolation segments 44, and between adjacent vane segments 23, help control the leakage flow.
  • An axial flow turbine comprising:
  • a rotor having an array of rotatable blades on its periphery, said rotatable blades being 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, said arcuate support segments and said inner casing having a track and channel interlock arrangement therebetween, said arcuate support segments and 6 said outer shroud portion of said stationary integral vane segments having a track and channel interlock arrangement therebetween, each arcuate support segment being fixedly attached at one point on its periphery to the inner casing to permit circumferential thermal expansion of said segments,
  • arcuate blade ring segments being supported radially outwardly of said rotatable blades by arcuate support segments having track and channel interlock arrangements with the inner casing and also having a track and channel interlocking support arrangement between an edge of each of said ring segments and the downstream edge of adjacent upstream stationary integral vane segments,
  • said inner casing being supported within said outer casing by generally horizontal keying members, said keying members being received in keyways within said outer casing,
  • each inner casing member and said outer casing providing vertical alignment of said inner casing member with respect to said turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00394599A 1973-09-05 1973-09-05 Axial flow turbine structure Expired - Lifetime US3841787A (en)

Priority Applications (10)

Application Number Priority Date Filing Date Title
US00394599A US3841787A (en) 1973-09-05 1973-09-05 Axial flow turbine structure
CA206,953A CA975300A (en) 1973-09-05 1974-08-13 Axial flow turbine structure
DE2439339A DE2439339C2 (de) 1973-09-05 1974-08-16 Gasturbine
NL7410982A NL7410982A (nl) 1973-09-05 1974-08-16 Axiaalstroomturbine.
CH1128174A CH583850A5 (nl) 1973-09-05 1974-08-19
GB3733274A GB1461965A (en) 1973-09-05 1974-08-27 Axial flow turbine structure
IT26782/74A IT1020335B (it) 1973-09-05 1974-08-30 Struttura per turbina a flusso assiale
JP10000474A JPS5337484B2 (nl) 1973-09-05 1974-09-02
SE7411255A SE392151B (sv) 1973-09-05 1974-09-05 Gasturbin
FR7430188A FR2242565B1 (nl) 1973-09-05 1974-09-05

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00394599A US3841787A (en) 1973-09-05 1973-09-05 Axial flow turbine structure

Publications (1)

Publication Number Publication Date
US3841787A true US3841787A (en) 1974-10-15

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ID=23559637

Family Applications (1)

Application Number Title Priority Date Filing Date
US00394599A Expired - Lifetime US3841787A (en) 1973-09-05 1973-09-05 Axial flow turbine structure

Country Status (10)

Country Link
US (1) US3841787A (nl)
JP (1) JPS5337484B2 (nl)
CA (1) CA975300A (nl)
CH (1) CH583850A5 (nl)
DE (1) DE2439339C2 (nl)
FR (1) FR2242565B1 (nl)
GB (1) GB1461965A (nl)
IT (1) IT1020335B (nl)
NL (1) NL7410982A (nl)
SE (1) SE392151B (nl)

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3892497A (en) * 1974-05-14 1975-07-01 Westinghouse Electric Corp Axial flow turbine stationary blade and blade ring locking arrangement
DE2621913A1 (de) * 1975-06-09 1976-12-23 United Technologies Corp Gasturbinentriebwerk
US4247248A (en) * 1978-12-20 1981-01-27 United Technologies Corporation Outer air seal support structure for gas turbine engine
US4511306A (en) * 1982-02-02 1985-04-16 Westinghouse Electric Corp. Combustion turbine single airfoil stator vane structure
US4816213A (en) * 1987-08-24 1989-03-28 Westinghouse Electric Corp. Thermal distortion isolation system for turbine blade rings
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
US5412939A (en) * 1993-12-20 1995-05-09 Alliedsignal Inc. Seal compression tool for gas turbine engine
US5492445A (en) * 1994-02-18 1996-02-20 Solar Turbines Incorporated Hook nozzle arrangement for supporting airfoil vanes
US5618161A (en) * 1995-10-17 1997-04-08 Westinghouse Electric Corporation Apparatus for restraining motion of a turbo-machine stationary vane
FR2761119A1 (fr) * 1997-03-20 1998-09-25 Snecma Stator de compresseur de turbomachine
US6517313B2 (en) 2001-06-25 2003-02-11 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
US6533542B2 (en) * 2001-01-15 2003-03-18 Mitsubishi Heavy Industries, Ltd. Split ring for gas turbine casing
US6659716B1 (en) * 2002-07-15 2003-12-09 Mitsubishi Heavy Industries, Ltd. Gas turbine having thermally insulating rings
US6896483B2 (en) 2001-07-02 2005-05-24 Allison Advanced Development Company Blade track assembly
WO2006100222A1 (de) * 2005-03-24 2006-09-28 Alstom Technology Ltd Leitschaufel für eine strömungsrotationsmaschine
US20070122270A1 (en) * 2003-12-19 2007-05-31 Gerhard Brueckner Turbomachine, especially a gas turbine
EP2163728A2 (en) * 2008-09-11 2010-03-17 General Electric Company Load pin for compressor square base stator and method of use
EP2218882A1 (de) * 2009-02-16 2010-08-18 Siemens Aktiengesellschaft Leitschaufelträgersystem
EP2530249A1 (en) * 2011-05-30 2012-12-05 Siemens Aktiengesellschaft Piston seal ring
US20120328423A1 (en) * 2011-06-20 2012-12-27 Mitsubishi Heavy Industries, Ltd. Gas turbine and repairing method of gas turbine
US20140023480A1 (en) * 2012-07-20 2014-01-23 Michael G. McCaffrey Radial position control of case supported structure
US20140093363A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Liner and method of assembly
US9291066B2 (en) 2013-11-11 2016-03-22 General Electric Company Methods and systems for sealing a rotary machine using a segmented seal ring
US20180087395A1 (en) * 2016-09-23 2018-03-29 Rolls-Royce Plc Gas turbine engine
US20180149030A1 (en) * 2016-11-30 2018-05-31 Rolls-Royce Corporation Turbine shroud with hanger attachment

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5974305A (ja) * 1982-10-21 1984-04-26 Hitachi Ltd ガスタ−ビンのシユラウド
FR2683851A1 (fr) * 1991-11-20 1993-05-21 Snecma Turbomachine equipee de moyens facilitant le reglage des jeux du stator entree stator et rotor.
US6773228B2 (en) * 2002-07-03 2004-08-10 General Electric Company Methods and apparatus for turbine nozzle locks
EP1389669B1 (de) * 2002-08-16 2006-06-07 Siemens Aktiengesellschaft Befestigungssystem
FR2960591B1 (fr) * 2010-06-01 2012-08-24 Snecma Dispositif pour caler en rotation un segment de distributeur dans un carter de turbomachine ; pion antirotation

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US2919891A (en) * 1957-06-17 1960-01-05 Gen Electric Gas turbine diaphragm assembly
US3427000A (en) * 1966-11-14 1969-02-11 Westinghouse Electric Corp Axial flow turbine structure
US3519366A (en) * 1968-05-22 1970-07-07 Westinghouse Electric Corp Turbine diaphragm seal structure
US3529903A (en) * 1968-11-29 1970-09-22 Westinghouse Electric Corp Nozzle blade structure
US3529904A (en) * 1968-10-28 1970-09-22 Westinghouse Electric Corp Diaphragm seal structure
US3542483A (en) * 1968-07-17 1970-11-24 Westinghouse Electric Corp Turbine stator structure
US3689174A (en) * 1971-01-11 1972-09-05 Westinghouse Electric Corp Axial flow turbine structure
US3781125A (en) * 1972-04-07 1973-12-25 Westinghouse Electric Corp Gas turbine nozzle vane structure

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US2919891A (en) * 1957-06-17 1960-01-05 Gen Electric Gas turbine diaphragm assembly
US3427000A (en) * 1966-11-14 1969-02-11 Westinghouse Electric Corp Axial flow turbine structure
US3519366A (en) * 1968-05-22 1970-07-07 Westinghouse Electric Corp Turbine diaphragm seal structure
US3542483A (en) * 1968-07-17 1970-11-24 Westinghouse Electric Corp Turbine stator structure
US3529904A (en) * 1968-10-28 1970-09-22 Westinghouse Electric Corp Diaphragm seal structure
US3529903A (en) * 1968-11-29 1970-09-22 Westinghouse Electric Corp Nozzle blade structure
US3689174A (en) * 1971-01-11 1972-09-05 Westinghouse Electric Corp Axial flow turbine structure
US3781125A (en) * 1972-04-07 1973-12-25 Westinghouse Electric Corp Gas turbine nozzle vane structure

Cited By (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3892497A (en) * 1974-05-14 1975-07-01 Westinghouse Electric Corp Axial flow turbine stationary blade and blade ring locking arrangement
DE2621913A1 (de) * 1975-06-09 1976-12-23 United Technologies Corp Gasturbinentriebwerk
US4247248A (en) * 1978-12-20 1981-01-27 United Technologies Corporation Outer air seal support structure for gas turbine engine
US4511306A (en) * 1982-02-02 1985-04-16 Westinghouse Electric Corp. Combustion turbine single airfoil stator vane structure
US4816213A (en) * 1987-08-24 1989-03-28 Westinghouse Electric Corp. Thermal distortion isolation system for turbine blade rings
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
US5412939A (en) * 1993-12-20 1995-05-09 Alliedsignal Inc. Seal compression tool for gas turbine engine
US5492445A (en) * 1994-02-18 1996-02-20 Solar Turbines Incorporated Hook nozzle arrangement for supporting airfoil vanes
US5618161A (en) * 1995-10-17 1997-04-08 Westinghouse Electric Corporation Apparatus for restraining motion of a turbo-machine stationary vane
FR2761119A1 (fr) * 1997-03-20 1998-09-25 Snecma Stator de compresseur de turbomachine
US6533542B2 (en) * 2001-01-15 2003-03-18 Mitsubishi Heavy Industries, Ltd. Split ring for gas turbine casing
US6517313B2 (en) 2001-06-25 2003-02-11 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
US6896483B2 (en) 2001-07-02 2005-05-24 Allison Advanced Development Company Blade track assembly
US6659716B1 (en) * 2002-07-15 2003-12-09 Mitsubishi Heavy Industries, Ltd. Gas turbine having thermally insulating rings
US7704042B2 (en) * 2003-12-19 2010-04-27 Mtu Aero Engines Gmbh Turbomachine, especially a gas turbine
US20070122270A1 (en) * 2003-12-19 2007-05-31 Gerhard Brueckner Turbomachine, especially a gas turbine
US7645118B2 (en) 2005-03-24 2010-01-12 Alstom Technology Ltd. Guide vane for rotary turbo machinery
WO2006100222A1 (de) * 2005-03-24 2006-09-28 Alstom Technology Ltd Leitschaufel für eine strömungsrotationsmaschine
US20080050230A1 (en) * 2005-03-24 2008-02-28 Alstom Technology Ltd. Guide vane for rotary turbo machinery
CN101672302B (zh) * 2008-09-11 2014-07-23 通用电气公司 用于压缩机方形基部定子的安装销及使用方法
EP2163728A2 (en) * 2008-09-11 2010-03-17 General Electric Company Load pin for compressor square base stator and method of use
EP2163728A3 (en) * 2008-09-11 2012-04-25 General Electric Company Load pin for compressor square base stator and method of use
EP2218882A1 (de) * 2009-02-16 2010-08-18 Siemens Aktiengesellschaft Leitschaufelträgersystem
RU2581287C2 (ru) * 2011-05-30 2016-04-20 Сименс Акциенгезелльшафт Газовая турбина и способ изготовления такой газовой турбины
US9422823B2 (en) 2011-05-30 2016-08-23 Siemens Aktiengesellschaft Piston seal ring
CN103562502A (zh) * 2011-05-30 2014-02-05 西门子公司 活塞密封环
WO2012163611A1 (en) * 2011-05-30 2012-12-06 Siemens Aktiengesellschaft Piston seal ring
CN103562502B (zh) * 2011-05-30 2015-11-25 西门子公司 活塞密封环
EP2530249A1 (en) * 2011-05-30 2012-12-05 Siemens Aktiengesellschaft Piston seal ring
US20120328423A1 (en) * 2011-06-20 2012-12-27 Mitsubishi Heavy Industries, Ltd. Gas turbine and repairing method of gas turbine
US9435226B2 (en) * 2011-06-20 2016-09-06 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine and repairing method of gas turbine
US20140023480A1 (en) * 2012-07-20 2014-01-23 Michael G. McCaffrey Radial position control of case supported structure
US9200530B2 (en) * 2012-07-20 2015-12-01 United Technologies Corporation Radial position control of case supported structure
US20140093363A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Liner and method of assembly
US9334756B2 (en) * 2012-09-28 2016-05-10 United Technologies Corporation Liner and method of assembly
US9291066B2 (en) 2013-11-11 2016-03-22 General Electric Company Methods and systems for sealing a rotary machine using a segmented seal ring
US20180087395A1 (en) * 2016-09-23 2018-03-29 Rolls-Royce Plc Gas turbine engine
US20180149030A1 (en) * 2016-11-30 2018-05-31 Rolls-Royce Corporation Turbine shroud with hanger attachment

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Publication number Publication date
CA975300A (en) 1975-09-30
JPS5337484B2 (nl) 1978-10-09
CH583850A5 (nl) 1977-01-14
FR2242565B1 (nl) 1981-05-22
NL7410982A (nl) 1975-03-07
DE2439339C2 (de) 1983-09-29
GB1461965A (en) 1977-01-19
JPS5053708A (nl) 1975-05-13
IT1020335B (it) 1977-12-20
SE7411255L (nl) 1975-04-14
SE392151B (sv) 1977-03-14
FR2242565A1 (nl) 1975-03-28
DE2439339A1 (de) 1975-03-06

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