US3867060A - Shroud assembly - Google Patents

Shroud assembly Download PDF

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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
Application number
US401455A
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English (en)
Inventor
Thomas R Huber
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US401455A priority Critical patent/US3867060A/en
Priority to CA205,865A priority patent/CA1004143A/en
Priority to DE2445705A priority patent/DE2445705C2/de
Priority to FR7432408A priority patent/FR2245852B1/fr
Priority to JP49110045A priority patent/JPS5757607B2/ja
Priority to IT27762/74A priority patent/IT1022359B/it
Priority to GB4215274A priority patent/GB1473719A/en
Application granted granted Critical
Publication of US3867060A publication Critical patent/US3867060A/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
    • 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)
US401455A 1973-09-27 1973-09-27 Shroud assembly Expired - Lifetime US3867060A (en)

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)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE621436A (fr) * 1961-09-04 1962-08-16

Patent Citations (2)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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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