US3867060A - Shroud assembly - Google Patents
Shroud assembly Download PDFInfo
- Publication number
- US3867060A US3867060A US401455A US40145573A US3867060A US 3867060 A US3867060 A US 3867060A US 401455 A US401455 A US 401455A US 40145573 A US40145573 A US 40145573A US 3867060 A US3867060 A US 3867060A
- Authority
- US
- United States
- Prior art keywords
- shroud
- outer casing
- seal
- radially
- shroud segment
- 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
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
Definitions
- ABSTRACT In a turbomachine, axial flow leakage of motive fluid between rotor blade tips and the inner circumference of the outer casing is sometimes prevented by utilizing an overlapping (labyrinth) seal and shroud assembly between the blade tips and the outer casing. Removal and assembly of the overlapping shroud seal in an annular, non-split outer casing is greatly facilitated by providing a plurality of shroud segments about the blade tip periphery and a radially outer clearance gap between the shroud segments and the outer casing whereby each shroud segment may be moved radially to unlap the seal and permit axial] removal of the seal without disturbing rotor elements.
- This invention relates in general to turbomachines and more particularly to a shroud assembly for a turbomachine of the type having a non-split annular outer casing.
- the rotor blades are surrounded at their peripheries by a circumferential shroud assembly attached to the outer casing of the turbomachine.
- the rotor blade tip and the shroud assembly are closely adjacent one another to form a seal which prevents axial leakage of the motive fluid between the blade tips and the outer casing.
- One type of seal is the so-called labyrinth seal wherein radially extending blade teeth overlap, in the axial direction, radially depending shroud teeth thereby forming an axial seal.
- the overlapping (labyrinth) seal was used exclusively in conjunction with a horizontally split outer casing comprising upper and lower casing halves including upper and lower shroud segments. Replacement of the upper segment was accomplished by removal of the upper casing half. Removal of the lower shroud segment required removal of the rotor, the entire process being costly and time-consuming. It has also now become desirable to employ an annular or non-split outer casing.
- the present invention describes a construction and method for removing an overlapping (labyrinth) type seal and shroud assembly from an outer casing without disturbing the rotor elements.
- a turbomachine including a rotor axially disposed within a non'split, annular outer casing, said rotor including a plurality of radially extending blades, each blade formed with a tip portion having at least one seal tooth and said outer casing including an annular recess adjacent said blade tip portions, an improved shroud assembly as hereinafter described.
- the shroud assembly includes a plurality of arcuate shroud segments disposed in said outer casing annular recess; each shroud segment including a radially depending shroud tooth which overlaps a respective blade tooth in the axial direction forming a labyrinth seal therewith.
- the annual recess is formed with an annular stop for radially locating said shroud segments relative to said blade tips. Moreover, a clearance gap remains between the radially outward portion of each shroud segment and the radially inward surface of said outer casing annular recess for receiving a spacer plate which bears against each shroud segment. Fastening means are provided for attaching each shroud segment to the outer casing. In assembly and disassembly operations, the spacer plate may be removed from said clearance gap whereby each shroud segment may be moved radially and axially.
- FIG. I is a cross section of a turbomachine (lower half removed) disclosing the details of the present invention.
- FIG. 2 is an enlarged cross section of a turbine blade and shroud assembly showing details according to the present invention.
- a turbomachine portion 11 includes annular outer casings 13 which may be axially joined at circumferential flanges 13a and 13b.
- the annular casings may be nozzle casings, exhaust casings, etc., as is well known in the art.
- the present invention finds its greatest utility in an annular or non-split outer casing, that is, a casing having no horizontal joint for assembly and disassembly. However, it will become apparent that the present invention may be applied to a horizontally split outer casing, if so desired.
- a rotor 15 is axially disposed within the outer casing and may include a high pressure wheel 17 and also a low pressure wheel 19. Each wheel contains radially extending blades 21 circumferentially mounted about the respective rotor wheels, as is well known in the art.
- FIG. 2 in conjunction with FIG. 1, shows a rotor blade 21 mounted within the outer casing 13.
- Each rotor blade includes a tip portion comprising a plurality of seal teeth 23.
- the blade seal teeth are disposed to extend radially. outward from the blade tip.
- the blade teeth form one portion of an axially extending labyrinth seal 25.
- the remaining portion of the labyrinth seal comprises an annular shroud assembly formed by a plurality of shroud segments 27 (only one shown) disposed radially outwardly of the blade seal teeth, and having radially depending shroud teeth 29 overlapping in the axial direction, the blade seal teeth.
- the shroud seal teeth extend radially inwardly between the radially outwardly extending blade teeth to create an interference in the axial direction.
- Each shroud segment is arcuate and the seal teeth may take the form of a number of arcuate rows.
- the shroud segments are disposed in an annular recess 31 formed in the outer casing.
- An annular stop means 33 extends axially into the annular recess.
- the shroud segment is formed with a mating recess 35 which abuts the stop means when. the shroud segment is properly seated into the annular recess.
- the mating recess 35 is elongated to permit radial movement of the shroud segment in the casing annular recess when the mating recess is proximate the stop means.
- Each shroud segment is also formed with an axial bore 41 therethrough whereas the outer casing also includes an aligned bore 43.
- a fastener 45 is threaded through the shroud bore and into the outer casing bore for fastening the shroud segment to the outer casing.
- Each shroud segment includes a radially outward surface 49 which is spaced from a radially inward surface 51 of the outer casing thereby defining an arcuate clearance 53 for allowing radial displacement of the shroud during assembly and disassembly.
- a spacer plate 55 is inserted into the clearance 53 for positioning the shroud segment radially inwardly toward the blade tips.
- each shroud segment may be inserted into a non-split annular turbomachine outer casing to form a labyrinth seal, in the axial direction, with rotor blade seal teeth while the rotor is axially positioned within the outer casing.
- Each shroud segment is axially inserted within the outer casing annular recess 31 until contact is made between the shroud segment and the rear wall of the annular recess defined by a depending portion of the outer casing as shown.
- Each shroud segment is held radially outward in the clearance 53 until the proper circumferential position as heretofore defined is achieved.
- each shroud segment is moved radially inward until annular stop 33 is contacted and the respective blade and shroud teeth are disposed in an axially overlapping position.
- Fasteners 45 are then inserted into bores 41 and 43 in the shroud segment and outer casing respectively.
- This assembly is the reverse of the aforementioned procedure whereby the shroud segment is moved radially outward to unlap the blade and shroud teeth and then axially removed.
- shroud segments may be assembled and removed without disturbing the rotor blades.
- a turbomachine including a rotor axially disposed within a unitary outer casing, said rotor formed with a plurality of radially extending rotor blades, each blade having at least one radially extending seal tooth; and, said outer casing being formed with an open end annular recess circumferentially adjacent said rotor blades seal teeth; a shroud assembly comprising:
- each shroud segment may be moved radially outward to unlap respective blade and shroud teeth prior to axial removal from the outer casing;
- each shroud segment for engaging a portion of said annular stop.
- a rotor axially disposed within an annular, non-split outer casing, said rotor formed with a plurality of radially extending rotor blades, each blade having radially extending seal teeth, and, said outer casing having an open end annular recess circumferentially adjacent said rotor blade seal teeth; a shroud assembly comprising:
- each shroudsegment including a plurality of radially depending shroud seal teeth which overlap said radially extending blade seal teeth in the axial direction forming an axial labyrinth seal therewith;
- each shroud segment for engaging a portion of said annular stop
- fastening means for attaching each shroud segment to the outer casing.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US401455A US3867060A (en) | 1973-09-27 | 1973-09-27 | Shroud assembly |
CA205,865A CA1004143A (en) | 1973-09-27 | 1974-07-29 | Shroud assembly |
DE2445705A DE2445705C2 (de) | 1973-09-27 | 1974-09-25 | Radialdichtring |
FR7432408A FR2245852B1 (fr) | 1973-09-27 | 1974-09-26 | |
JP49110045A JPS5757607B2 (fr) | 1973-09-27 | 1974-09-26 | |
IT27762/74A IT1022359B (it) | 1973-09-27 | 1974-09-26 | Fascia a segmenti per turbomacchina |
GB4215274A GB1473719A (en) | 1973-09-27 | 1974-09-27 | Turbomachines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US401455A US3867060A (en) | 1973-09-27 | 1973-09-27 | Shroud assembly |
Publications (1)
Publication Number | Publication Date |
---|---|
US3867060A true US3867060A (en) | 1975-02-18 |
Family
ID=23587839
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US401455A Expired - Lifetime US3867060A (en) | 1973-09-27 | 1973-09-27 | Shroud assembly |
Country Status (7)
Country | Link |
---|---|
US (1) | US3867060A (fr) |
JP (1) | JPS5757607B2 (fr) |
CA (1) | CA1004143A (fr) |
DE (1) | DE2445705C2 (fr) |
FR (1) | FR2245852B1 (fr) |
GB (1) | GB1473719A (fr) |
IT (1) | IT1022359B (fr) |
Cited By (37)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2470269A1 (fr) * | 1979-11-27 | 1981-05-29 | Snecma | Structure de retention pour carter de compresseur d'une turbomachine |
FR2483008A1 (fr) * | 1980-05-24 | 1981-11-27 | Mtu Muenchen Gmbh | Dispositif pour minimiser et maintenir constant le jeu d'extremite des aubes de turbines axiales de moteurs a turbines a gaz |
US4697978A (en) * | 1984-07-26 | 1987-10-06 | Matsushita Electric Industrial Co., Ltd. | Industrial robot |
US4941801A (en) * | 1988-03-23 | 1990-07-17 | Aisin Seiki Kabushiki Kaisha | Double water pump device |
US5037273A (en) * | 1988-12-19 | 1991-08-06 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Compressor impeller |
US5362072A (en) * | 1992-12-21 | 1994-11-08 | Imo Industries, Inc., Quabbin Division | Turbine radial adjustable labyrinth seal |
US5501573A (en) * | 1993-01-29 | 1996-03-26 | Steam Specialties, Inc. | Segmented seal assembly and method for retrofitting the same to turbines and the like |
US5632598A (en) * | 1995-01-17 | 1997-05-27 | Dresser-Rand | Shrouded axial flow turbo machine utilizing multiple labrinth seals |
WO2000058607A1 (fr) * | 1999-03-31 | 2000-10-05 | Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie 'nauchno-Proizvodstvennoe Predpriyatie 'motor' | Garniture d'etancheite a nid d'abeilles destinee de preference a une turbine a vapeur |
US6632069B1 (en) * | 2001-10-02 | 2003-10-14 | Oleg Naljotov | Step of pressure of the steam and gas turbine with universal belt |
US20030194322A1 (en) * | 2002-04-16 | 2003-10-16 | Herbert Brandl | Moving blade for a turbomachine |
US20040101410A1 (en) * | 2001-10-02 | 2004-05-27 | Oleg Naljotov | Axial flow fluid machine |
US20040156722A1 (en) * | 2003-02-06 | 2004-08-12 | Kafu Chu | Method and apparatus to facilitate reducing steam leakage |
US20050058539A1 (en) * | 2003-09-12 | 2005-03-17 | Siemens Westinghouse Power Corporation | Turbine blade tip clearance control device |
US20060133928A1 (en) * | 2004-12-22 | 2006-06-22 | General Electric Company | Removable abradable seal carriers for sealing between rotary and stationary turbine components |
US20060277922A1 (en) * | 2005-06-09 | 2006-12-14 | Pratt & Whitney Canada Corp. | Turbine support case and method of manufacturing |
US20070040335A1 (en) * | 2005-08-22 | 2007-02-22 | General Electric Company | Axially adjustable sealing ring |
US20070063449A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Stationary seal ring for a centrifugal compressor |
US20070065276A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Impeller for a centrifugal compressor |
US20070065277A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Centrifugal compressor including a seal system |
FR2927685A1 (fr) * | 2008-02-18 | 2009-08-21 | Gen Electric | Ensemble de bague d'etancheite et moteur a turbine comportant un tel ensemble |
US20110070072A1 (en) * | 2009-09-23 | 2011-03-24 | General Electric Company | Rotary machine tip clearance control mechanism |
US20110068540A1 (en) * | 2009-09-22 | 2011-03-24 | Colson Darryl A | Staggered seal assembly |
CN101220757B (zh) * | 2007-01-09 | 2013-03-27 | 株式会社东芝 | 汽轮机 |
CN103184900A (zh) * | 2012-01-03 | 2013-07-03 | 通用电气公司 | 用于涡轮护罩的向前台阶蜂巢式密封件 |
US20130189106A1 (en) * | 2012-01-20 | 2013-07-25 | General Electric Company | Turbomachine blade tip shroud |
US20130330179A1 (en) * | 2012-06-08 | 2013-12-12 | Rohit Chouhan | Shroud for a rotary machine and methods of assembling same |
US20140079538A1 (en) * | 2012-09-11 | 2014-03-20 | Sanji Ekanayake | Replaceable seals for turbine engine components and methods for installing the same |
US20140286766A1 (en) * | 2012-09-11 | 2014-09-25 | General Electric Company | Compressor Casing Assembly Providing Access To Compressor Blade Sealing Assembly |
US20150176422A1 (en) * | 2012-06-25 | 2015-06-25 | Borgwarner Inc. | Exhaust-gas turbocharger |
CN105408633A (zh) * | 2013-07-09 | 2016-03-16 | 萨乐锐伊塔洛工业有限公司 | 用于内燃机的可调节冷却泵 |
US9885368B2 (en) | 2012-05-24 | 2018-02-06 | Carrier Corporation | Stall margin enhancement of axial fan with rotating shroud |
US20180142567A1 (en) * | 2016-11-18 | 2018-05-24 | MTU Aero Engines AG | Sealing system for an axial turbomachine and axial turbomachine |
FR3068070A1 (fr) * | 2017-06-26 | 2018-12-28 | Safran Aircraft Engines | Turbine pour turbomachine |
US10323537B2 (en) * | 2015-10-02 | 2019-06-18 | DOOSAN Heavy Industries Construction Co., LTD | Gas turbine tip clearance control assembly |
CN111691927A (zh) * | 2020-05-22 | 2020-09-22 | 哈尔滨工业大学 | 涡轮机及涡轮机叶顶间隙密封结构 |
US20230019443A1 (en) * | 2019-12-12 | 2023-01-19 | Nuovo Pignone Tecnologie - S.R.L. | Composite seal structure for a machine, and method of manufacturing the composite seal structure |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5449407U (fr) * | 1977-09-13 | 1979-04-05 | ||
DE19738671B4 (de) * | 1997-09-04 | 2007-03-01 | Alstom | Dichtungsanordnung |
DE19850732A1 (de) | 1998-11-04 | 2000-05-11 | Asea Brown Boveri | Axialturbine |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2416268A (en) * | 1943-10-01 | 1947-02-18 | Allis Chalmers Mfg Co | Hydraulic turbine seal |
US2956733A (en) * | 1954-09-28 | 1960-10-18 | Stalker Corp | Fluid turning wheels for compressors |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE621436A (fr) * | 1961-09-04 | 1962-08-16 |
-
1973
- 1973-09-27 US US401455A patent/US3867060A/en not_active Expired - Lifetime
-
1974
- 1974-07-29 CA CA205,865A patent/CA1004143A/en not_active Expired
- 1974-09-25 DE DE2445705A patent/DE2445705C2/de not_active Expired
- 1974-09-26 IT IT27762/74A patent/IT1022359B/it active
- 1974-09-26 JP JP49110045A patent/JPS5757607B2/ja not_active Expired
- 1974-09-26 FR FR7432408A patent/FR2245852B1/fr not_active Expired
- 1974-09-27 GB GB4215274A patent/GB1473719A/en not_active Expired
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2416268A (en) * | 1943-10-01 | 1947-02-18 | Allis Chalmers Mfg Co | Hydraulic turbine seal |
US2956733A (en) * | 1954-09-28 | 1960-10-18 | Stalker Corp | Fluid turning wheels for compressors |
Cited By (56)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2470269A1 (fr) * | 1979-11-27 | 1981-05-29 | Snecma | Structure de retention pour carter de compresseur d'une turbomachine |
EP0030179A1 (fr) * | 1979-11-27 | 1981-06-10 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Structure de rétention pour carter de compresseur d'une turbomachine |
FR2483008A1 (fr) * | 1980-05-24 | 1981-11-27 | Mtu Muenchen Gmbh | Dispositif pour minimiser et maintenir constant le jeu d'extremite des aubes de turbines axiales de moteurs a turbines a gaz |
US4697978A (en) * | 1984-07-26 | 1987-10-06 | Matsushita Electric Industrial Co., Ltd. | Industrial robot |
US4941801A (en) * | 1988-03-23 | 1990-07-17 | Aisin Seiki Kabushiki Kaisha | Double water pump device |
US5037273A (en) * | 1988-12-19 | 1991-08-06 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Compressor impeller |
US5362072A (en) * | 1992-12-21 | 1994-11-08 | Imo Industries, Inc., Quabbin Division | Turbine radial adjustable labyrinth seal |
US5501573A (en) * | 1993-01-29 | 1996-03-26 | Steam Specialties, Inc. | Segmented seal assembly and method for retrofitting the same to turbines and the like |
US5632598A (en) * | 1995-01-17 | 1997-05-27 | Dresser-Rand | Shrouded axial flow turbo machine utilizing multiple labrinth seals |
WO2000058607A1 (fr) * | 1999-03-31 | 2000-10-05 | Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie 'nauchno-Proizvodstvennoe Predpriyatie 'motor' | Garniture d'etancheite a nid d'abeilles destinee de preference a une turbine a vapeur |
US6632069B1 (en) * | 2001-10-02 | 2003-10-14 | Oleg Naljotov | Step of pressure of the steam and gas turbine with universal belt |
US20040101410A1 (en) * | 2001-10-02 | 2004-05-27 | Oleg Naljotov | Axial flow fluid machine |
US20030194322A1 (en) * | 2002-04-16 | 2003-10-16 | Herbert Brandl | Moving blade for a turbomachine |
US6962484B2 (en) * | 2002-04-16 | 2005-11-08 | Alstom Technology Ltd | Moving blade for a turbomachine |
US6776577B1 (en) * | 2003-02-06 | 2004-08-17 | General Electric Company | Method and apparatus to facilitate reducing steam leakage |
US20040156722A1 (en) * | 2003-02-06 | 2004-08-12 | Kafu Chu | Method and apparatus to facilitate reducing steam leakage |
US20050058539A1 (en) * | 2003-09-12 | 2005-03-17 | Siemens Westinghouse Power Corporation | Turbine blade tip clearance control device |
US6926495B2 (en) * | 2003-09-12 | 2005-08-09 | Siemens Westinghouse Power Corporation | Turbine blade tip clearance control device |
US7287956B2 (en) * | 2004-12-22 | 2007-10-30 | General Electric Company | Removable abradable seal carriers for sealing between rotary and stationary turbine components |
US20060133928A1 (en) * | 2004-12-22 | 2006-06-22 | General Electric Company | Removable abradable seal carriers for sealing between rotary and stationary turbine components |
US20060277922A1 (en) * | 2005-06-09 | 2006-12-14 | Pratt & Whitney Canada Corp. | Turbine support case and method of manufacturing |
US7909569B2 (en) * | 2005-06-09 | 2011-03-22 | Pratt & Whitney Canada Corp. | Turbine support case and method of manufacturing |
US20070040335A1 (en) * | 2005-08-22 | 2007-02-22 | General Electric Company | Axially adjustable sealing ring |
US20070063449A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Stationary seal ring for a centrifugal compressor |
US20070065276A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Impeller for a centrifugal compressor |
US20070065277A1 (en) * | 2005-09-19 | 2007-03-22 | Ingersoll-Rand Company | Centrifugal compressor including a seal system |
CN101220757B (zh) * | 2007-01-09 | 2013-03-27 | 株式会社东芝 | 汽轮机 |
FR2927685A1 (fr) * | 2008-02-18 | 2009-08-21 | Gen Electric | Ensemble de bague d'etancheite et moteur a turbine comportant un tel ensemble |
JP2009191850A (ja) * | 2008-02-18 | 2009-08-27 | General Electric Co <Ge> | 蒸気タービンエンジンとその組立方法 |
US20110068540A1 (en) * | 2009-09-22 | 2011-03-24 | Colson Darryl A | Staggered seal assembly |
US8083236B2 (en) * | 2009-09-22 | 2011-12-27 | Hamilton Sundstrand Corporation | Staggered seal assembly |
US20110070072A1 (en) * | 2009-09-23 | 2011-03-24 | General Electric Company | Rotary machine tip clearance control mechanism |
US20130170962A1 (en) * | 2012-01-03 | 2013-07-04 | General Electric Company | Forward Step Honeycomb Seal for Turbine Shroud |
US9476317B2 (en) | 2012-01-03 | 2016-10-25 | General Electric Company | Forward step honeycomb seal for turbine shroud |
CN103184900A (zh) * | 2012-01-03 | 2013-07-03 | 通用电气公司 | 用于涡轮护罩的向前台阶蜂巢式密封件 |
US9080459B2 (en) * | 2012-01-03 | 2015-07-14 | General Electric Company | Forward step honeycomb seal for turbine shroud |
CN103184900B (zh) * | 2012-01-03 | 2017-10-24 | 通用电气公司 | 用于涡轮护罩的向前台阶蜂巢式密封件 |
US20130189106A1 (en) * | 2012-01-20 | 2013-07-25 | General Electric Company | Turbomachine blade tip shroud |
US9109455B2 (en) * | 2012-01-20 | 2015-08-18 | General Electric Company | Turbomachine blade tip shroud |
US9885368B2 (en) | 2012-05-24 | 2018-02-06 | Carrier Corporation | Stall margin enhancement of axial fan with rotating shroud |
US20130330179A1 (en) * | 2012-06-08 | 2013-12-12 | Rohit Chouhan | Shroud for a rotary machine and methods of assembling same |
US8936431B2 (en) * | 2012-06-08 | 2015-01-20 | General Electric Company | Shroud for a rotary machine and methods of assembling same |
US10119411B2 (en) * | 2012-06-25 | 2018-11-06 | Borgwarner Inc. | Exhaust-gas turbocharger |
US20150176422A1 (en) * | 2012-06-25 | 2015-06-25 | Borgwarner Inc. | Exhaust-gas turbocharger |
US20140079538A1 (en) * | 2012-09-11 | 2014-03-20 | Sanji Ekanayake | Replaceable seals for turbine engine components and methods for installing the same |
US9309776B2 (en) * | 2012-09-11 | 2016-04-12 | General Electric Company | Replaceable seals for turbine engine components and methods for installing the same |
US20140286766A1 (en) * | 2012-09-11 | 2014-09-25 | General Electric Company | Compressor Casing Assembly Providing Access To Compressor Blade Sealing Assembly |
CN105408633A (zh) * | 2013-07-09 | 2016-03-16 | 萨乐锐伊塔洛工业有限公司 | 用于内燃机的可调节冷却泵 |
US10323537B2 (en) * | 2015-10-02 | 2019-06-18 | DOOSAN Heavy Industries Construction Co., LTD | Gas turbine tip clearance control assembly |
US20180142567A1 (en) * | 2016-11-18 | 2018-05-24 | MTU Aero Engines AG | Sealing system for an axial turbomachine and axial turbomachine |
FR3068070A1 (fr) * | 2017-06-26 | 2018-12-28 | Safran Aircraft Engines | Turbine pour turbomachine |
EP3421730A1 (fr) * | 2017-06-26 | 2019-01-02 | Safran Aircraft Engines | Turbine pour turbomachine avec anneau d'étanchéité comportant deux parties |
US10760441B2 (en) | 2017-06-26 | 2020-09-01 | Safran Aircraft Engines | Turbine for a turbine engine |
US20230019443A1 (en) * | 2019-12-12 | 2023-01-19 | Nuovo Pignone Tecnologie - S.R.L. | Composite seal structure for a machine, and method of manufacturing the composite seal structure |
US11927099B2 (en) * | 2019-12-12 | 2024-03-12 | Nuovo Pignone Tecnologie—S.R.L. | Composite seal structure for a machine, and method of manufacturing the composite seal structure |
CN111691927A (zh) * | 2020-05-22 | 2020-09-22 | 哈尔滨工业大学 | 涡轮机及涡轮机叶顶间隙密封结构 |
Also Published As
Publication number | Publication date |
---|---|
GB1473719A (en) | 1977-05-18 |
JPS5077704A (fr) | 1975-06-25 |
DE2445705A1 (de) | 1975-04-10 |
FR2245852A1 (fr) | 1975-04-25 |
DE2445705C2 (de) | 1984-05-17 |
CA1004143A (en) | 1977-01-25 |
FR2245852B1 (fr) | 1980-09-05 |
IT1022359B (it) | 1978-03-20 |
JPS5757607B2 (fr) | 1982-12-06 |
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