GB2261708B - Turbo-shaft engine stator - Google Patents

Turbo-shaft engine stator

Info

Publication number
GB2261708B
GB2261708B GB9224411A GB9224411A GB2261708B GB 2261708 B GB2261708 B GB 2261708B GB 9224411 A GB9224411 A GB 9224411A GB 9224411 A GB9224411 A GB 9224411A GB 2261708 B GB2261708 B GB 2261708B
Authority
GB
United Kingdom
Prior art keywords
turbo
shaft engine
engine stator
stator
shaft
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 - Fee Related
Application number
GB9224411A
Other languages
English (en)
Other versions
GB9224411D0 (en
GB2261708A (en
Inventor
Alain Marc Lucien Bromann
Jean-Louis Charbonnel
Pierre Debeneix
Daniel Jean Marey
Jacky Serge Naudet
Thierry Jean Maurice Niclot
Yann Rigaud
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB9224411D0 publication Critical patent/GB9224411D0/en
Publication of GB2261708A publication Critical patent/GB2261708A/en
Application granted granted Critical
Publication of GB2261708B publication Critical patent/GB2261708B/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • 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
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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

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)
GB9224411A 1991-11-20 1992-11-20 Turbo-shaft engine stator Expired - Fee Related GB2261708B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR9114290A FR2683851A1 (fr) 1991-11-20 1991-11-20 Turbomachine equipee de moyens facilitant le reglage des jeux du stator entree stator et rotor.

Publications (3)

Publication Number Publication Date
GB9224411D0 GB9224411D0 (en) 1993-01-13
GB2261708A GB2261708A (en) 1993-05-26
GB2261708B true GB2261708B (en) 1995-01-25

Family

ID=9419136

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9224411A Expired - Fee Related GB2261708B (en) 1991-11-20 1992-11-20 Turbo-shaft engine stator

Country Status (3)

Country Link
US (1) US5288206A (enExample)
FR (1) FR2683851A1 (enExample)
GB (1) GB2261708B (enExample)

Families Citing this family (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2711730B1 (fr) * 1993-10-27 1995-12-01 Snecma Turbomachine équipée de moyens de pilotage des jeux entre rotor et stator.
US5653581A (en) * 1994-11-29 1997-08-05 United Technologies Corporation Case-tied joint for compressor stators
US5961278A (en) * 1997-12-17 1999-10-05 Pratt & Whitney Canada Inc. Housing for turbine assembly
US6059525A (en) * 1998-05-19 2000-05-09 General Electric Co. Low strain shroud for a turbine technical field
FR2780443B1 (fr) 1998-06-25 2000-08-04 Snecma Anneau de stator de turbine haute pression d'une turbomachine
WO2000057033A1 (de) * 1999-03-24 2000-09-28 Siemens Aktiengesellschaft Abdeckelement und anordnung mit einem abdeckelement und mit einer tragstruktur
US6325596B1 (en) * 2000-07-21 2001-12-04 General Electric Company Turbine diaphragm support system
FR2817285B1 (fr) 2000-11-30 2003-06-13 Snecma Moteurs Virole interne de stator
FR2829176B1 (fr) * 2001-08-30 2005-06-24 Snecma Moteurs Carter de stator de turbomachine
FR2835563B1 (fr) * 2002-02-07 2004-04-02 Snecma Moteurs Agencement d'accrochage de secteurs en arc de cercle de distributeur porteur d'aubes
FR2852053B1 (fr) 2003-03-06 2007-12-28 Snecma Moteurs Turbine haute pression pour turbomachine
GB0318609D0 (en) * 2003-08-08 2003-09-10 Rolls Royce Plc An arrangement for mounting a non-rotating component
ATE503914T1 (de) * 2004-05-17 2011-04-15 Carlton Forge Works Turbinengehäuseverstärkung bei einem gasturbinentriebwerk
FR2875535B1 (fr) * 2004-09-21 2009-10-30 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz
US8191254B2 (en) * 2004-09-23 2012-06-05 Carlton Forge Works Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
DE102005045255A1 (de) * 2005-09-22 2007-03-29 Mtu Aero Engines Gmbh Verbesserter Verdichter in Axialbauart
US7762761B2 (en) * 2005-11-30 2010-07-27 General Electric Company Methods and apparatus for assembling turbine nozzles
FR2897121B1 (fr) * 2006-02-09 2008-05-02 Snecma Sa Dispositif de reglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine
US8393855B2 (en) * 2007-06-29 2013-03-12 General Electric Company Flange with axially curved impingement surface for gas turbine engine clearance control
US8197186B2 (en) 2007-06-29 2012-06-12 General Electric Company Flange with axially extending holes for gas turbine engine clearance control
EP2159382A1 (de) * 2008-08-27 2010-03-03 Siemens Aktiengesellschaft Leitschaufelträger für eine Gasturbine
EP2473712B1 (en) 2009-09-02 2013-07-03 Siemens Aktiengesellschaft A mounting apparatus
RU2490478C2 (ru) * 2011-10-11 2013-08-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Статор турбомашины
EP2719869A1 (de) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Axiale Abdichtung in einer Gehäusestruktur für eine Strömungsmaschine
FR3010048B1 (fr) * 2013-09-04 2017-03-31 Snecma Structure de liaison moteur-nacelle a cales de liaison
US10436070B2 (en) * 2013-09-11 2019-10-08 United Technologies Corporation Blade outer air seal having angled retention hook
JP6223774B2 (ja) * 2013-10-15 2017-11-01 三菱日立パワーシステムズ株式会社 ガスタービン
RU2567892C1 (ru) * 2014-06-02 2015-11-10 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Статор компрессора высокого давления
US10215099B2 (en) * 2015-02-06 2019-02-26 United Technologies Corporation System and method for limiting movement of a retainer ring of a gas turbine engine
US9856753B2 (en) * 2015-06-10 2018-01-02 United Technologies Corporation Inner diameter scallop case flange for a case of a gas turbine engine
US10697314B2 (en) 2016-10-14 2020-06-30 Rolls-Royce Corporation Turbine shroud with I-beam construction
US10920609B2 (en) * 2017-04-25 2021-02-16 Safran Aircraft Engines Turbine engine turbine assembly
US10557365B2 (en) 2017-10-05 2020-02-11 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having reaction load distribution features
US20200072070A1 (en) * 2018-09-05 2020-03-05 United Technologies Corporation Unified boas support and vane platform
US11149563B2 (en) 2019-10-04 2021-10-19 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having axial reaction load distribution features

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB761829A (en) * 1954-02-04 1956-11-21 George Frederick Kelk Stator ring assembly for a rotary bladed fluid flow machine
GB1461965A (en) * 1973-09-05 1977-01-19 Westinghouse Electric Corp Axial flow turbine structure
GB2019954A (en) * 1978-04-04 1979-11-07 Rolls Royce Turbomachine housing
GB2076067A (en) * 1980-05-16 1981-11-25 Mtu Muenchen Gmbh Axial-flow compressor or turbine outer casing
GB2115487A (en) * 1982-02-19 1983-09-07 Gen Electric Double wall compressor casing
GB2144492A (en) * 1983-08-01 1985-03-06 United Technologies Corp Stator assembly for bounding the flow path of a gas turbine engine
GB2240818A (en) * 1990-02-12 1991-08-14 Gen Electric Blade tip clearance control apparatus in a gas turbine engine
EP0475771A1 (en) * 1990-09-12 1992-03-18 United Technologies Corporation Compressor case construction

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE461534A (enExample) * 1945-07-10
US2834537A (en) * 1954-01-18 1958-05-13 Ryan Aeronautical Co Compressor stator structure
US2858104A (en) * 1954-02-04 1958-10-28 A V Roe Canada Ltd Adjustable gas turbine shroud ring segments
GB799896A (en) * 1955-10-21 1958-08-13 Rolls Royce Improvements in or relating to axial-flow compressors
GB804922A (en) * 1956-01-13 1958-11-26 Rolls Royce Improvements in or relating to axial-flow fluid machines for example compressors andturbines
US2928556A (en) * 1957-12-24 1960-03-15 United Hoisting Company Wall hoister
NL269161A (enExample) * 1960-09-28
DE1426818A1 (de) * 1963-07-26 1969-03-13 Licentia Gmbh Einrichtung zur Radialverstellung von Segmenten eines Ringes einer Axialturbomaschine,insbesondere -gasturbine,der Leitschaufeln traegt und/oder Laufschaufeln umgibt
GB2103294B (en) * 1981-07-11 1984-08-30 Rolls Royce Shroud assembly for a gas turbine engine
GB2169962B (en) * 1985-01-22 1988-07-13 Rolls Royce Blade tip clearance control
DE8507551U1 (de) * 1985-03-14 1990-10-11 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Strömungsmaschine mit Mitteln zur Kontrolle des Radialspaltes
DE3546839C2 (de) * 1985-11-19 1995-05-04 Mtu Muenchen Gmbh Gasturbinenstrahltriebwerk in Mehrwellen-Zweistrombauweise
US4921401A (en) * 1989-02-23 1990-05-01 United Technologies Corporation Casting for a rotary machine
US5127793A (en) * 1990-05-31 1992-07-07 General Electric Company Turbine shroud clearance control assembly
US5197856A (en) * 1991-06-24 1993-03-30 General Electric Company Compressor stator
US5141395A (en) * 1991-09-05 1992-08-25 General Electric Company Flow activated flowpath liner seal

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB761829A (en) * 1954-02-04 1956-11-21 George Frederick Kelk Stator ring assembly for a rotary bladed fluid flow machine
GB1461965A (en) * 1973-09-05 1977-01-19 Westinghouse Electric Corp Axial flow turbine structure
GB2019954A (en) * 1978-04-04 1979-11-07 Rolls Royce Turbomachine housing
GB2076067A (en) * 1980-05-16 1981-11-25 Mtu Muenchen Gmbh Axial-flow compressor or turbine outer casing
GB2115487A (en) * 1982-02-19 1983-09-07 Gen Electric Double wall compressor casing
GB2144492A (en) * 1983-08-01 1985-03-06 United Technologies Corp Stator assembly for bounding the flow path of a gas turbine engine
GB2240818A (en) * 1990-02-12 1991-08-14 Gen Electric Blade tip clearance control apparatus in a gas turbine engine
EP0475771A1 (en) * 1990-09-12 1992-03-18 United Technologies Corporation Compressor case construction

Also Published As

Publication number Publication date
FR2683851A1 (fr) 1993-05-21
FR2683851B1 (enExample) 1995-03-31
GB9224411D0 (en) 1993-01-13
GB2261708A (en) 1993-05-26
US5288206A (en) 1994-02-22

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Legal Events

Date Code Title Description
732E Amendments to the register in respect of changes of name or changes affecting rights (sect. 32/1977)

Free format text: REGISTERED BETWEEN 20120517 AND 20120523

PCNP Patent ceased through non-payment of renewal fee

Effective date: 20111120