FR2578291B1 - Systeme de reglage de l'espace libre de tete de pale d'un compresseur de moteur a turbine a gaz - Google Patents

Systeme de reglage de l'espace libre de tete de pale d'un compresseur de moteur a turbine a gaz

Info

Publication number
FR2578291B1
FR2578291B1 FR868600846A FR8600846A FR2578291B1 FR 2578291 B1 FR2578291 B1 FR 2578291B1 FR 868600846 A FR868600846 A FR 868600846A FR 8600846 A FR8600846 A FR 8600846A FR 2578291 B1 FR2578291 B1 FR 2578291B1
Authority
FR
France
Prior art keywords
adjusting
gas turbine
head space
blade head
turbine compressor
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
FR868600846A
Other languages
English (en)
Other versions
FR2578291A1 (fr
Inventor
William Butler Wright
Richard James Flatman
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of FR2578291A1 publication Critical patent/FR2578291A1/fr
Application granted granted Critical
Publication of FR2578291B1 publication Critical patent/FR2578291B1/fr
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
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
FR868600846A 1985-01-22 1986-01-22 Systeme de reglage de l'espace libre de tete de pale d'un compresseur de moteur a turbine a gaz Expired - Fee Related FR2578291B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB08501554A GB2169962B (en) 1985-01-22 1985-01-22 Blade tip clearance control

Publications (2)

Publication Number Publication Date
FR2578291A1 FR2578291A1 (fr) 1986-09-05
FR2578291B1 true FR2578291B1 (fr) 1990-01-19

Family

ID=10573218

Family Applications (1)

Application Number Title Priority Date Filing Date
FR868600846A Expired - Fee Related FR2578291B1 (fr) 1985-01-22 1986-01-22 Systeme de reglage de l'espace libre de tete de pale d'un compresseur de moteur a turbine a gaz

Country Status (5)

Country Link
US (1) US4683716A (fr)
JP (1) JPS61185602A (fr)
DE (1) DE3601546A1 (fr)
FR (1) FR2578291B1 (fr)
GB (1) GB2169962B (fr)

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GB2195715B (en) * 1986-10-08 1990-10-10 Rolls Royce Plc Gas turbine engine rotor blade clearance control
US4826397A (en) * 1988-06-29 1989-05-02 United Technologies Corporation Stator assembly for a gas turbine engine
US5048288A (en) * 1988-12-20 1991-09-17 United Technologies Corporation Combined turbine stator cooling and turbine tip clearance control
FR2640687B1 (fr) * 1988-12-21 1991-02-08 Snecma Carter de compresseur de turbomachine a pilotage de son diametre interne
US4971517A (en) * 1988-12-27 1990-11-20 Allied-Signal Inc. Turbine blade clearance controller
GB8907706D0 (en) * 1989-04-05 1989-05-17 Rolls Royce Plc An axial flow compressor
US5096375A (en) * 1989-09-08 1992-03-17 General Electric Company Radial adjustment mechanism for blade tip clearance control apparatus
US5018942A (en) * 1989-09-08 1991-05-28 General Electric Company Mechanical blade tip clearance control apparatus for a gas turbine engine
US5104287A (en) * 1989-09-08 1992-04-14 General Electric Company Blade tip clearance control apparatus for a gas turbine engine
US5056986A (en) * 1989-11-22 1991-10-15 Westinghouse Electric Corp. Inner cylinder axial positioning system
US5054997A (en) * 1989-11-22 1991-10-08 General Electric Company Blade tip clearance control apparatus using bellcrank mechanism
US5056988A (en) * 1990-02-12 1991-10-15 General Electric Company Blade tip clearance control apparatus using shroud segment position modulation
US5049033A (en) * 1990-02-20 1991-09-17 General Electric Company Blade tip clearance control apparatus using cam-actuated shroud segment positioning mechanism
US5116199A (en) * 1990-12-20 1992-05-26 General Electric Company Blade tip clearance control apparatus using shroud segment annular support ring thermal expansion
US5228828A (en) * 1991-02-15 1993-07-20 General Electric Company Gas turbine engine clearance control apparatus
GB9103809D0 (en) * 1991-02-23 1991-04-10 Rolls Royce Plc Blade tip clearance control apparatus
US5263816A (en) * 1991-09-03 1993-11-23 General Motors Corporation Turbomachine with active tip clearance control
FR2683002B1 (fr) * 1991-10-23 1993-12-17 Snecma Compresseur axial adapte a la maintenance et son procede de maintenance.
FR2683851A1 (fr) * 1991-11-20 1993-05-21 Snecma Turbomachine equipee de moyens facilitant le reglage des jeux du stator entree stator et rotor.
US5344284A (en) * 1993-03-29 1994-09-06 The United States Of America As Represented By The Secretary Of The Air Force Adjustable clearance control for rotor blade tips in a gas turbine engine
US5685693A (en) * 1995-03-31 1997-11-11 General Electric Co. Removable inner turbine shell with bucket tip clearance control
GB2313414B (en) * 1996-05-24 2000-05-17 Rolls Royce Plc Gas turbine engine blade tip clearance control
GB9725623D0 (en) 1997-12-03 2006-09-20 Rolls Royce Plc Improvements in or relating to a blade tip clearance system
US6884026B2 (en) * 2002-09-30 2005-04-26 General Electric Company Turbine engine shroud assembly including axially floating shroud segment
US20040219011A1 (en) * 2003-05-02 2004-11-04 General Electric Company High pressure turbine elastic clearance control system and method
US7596954B2 (en) 2004-07-09 2009-10-06 United Technologies Corporation Blade clearance control
US8011883B2 (en) * 2004-12-29 2011-09-06 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method
DE102005030426A1 (de) * 2005-06-30 2007-01-04 Mtu Aero Engines Gmbh Rotorspalt Steuervorrichtung für einen Verdichter
DE102006052786B4 (de) * 2006-11-09 2011-06-30 MTU Aero Engines GmbH, 80995 Turbomaschine
US8616827B2 (en) * 2008-02-20 2013-12-31 Rolls-Royce Corporation Turbine blade tip clearance system
US8256228B2 (en) * 2008-04-29 2012-09-04 Rolls Royce Corporation Turbine blade tip clearance apparatus and method
US8092146B2 (en) * 2009-03-26 2012-01-10 Pratt & Whitney Canada Corp. Active tip clearance control arrangement for gas turbine engine
GB0910070D0 (en) 2009-06-12 2009-07-22 Rolls Royce Plc System and method for adjusting rotor-stator clearance
GB201004381D0 (en) * 2010-03-17 2010-04-28 Rolls Royce Plc Rotor blade tip clearance control
US9458855B2 (en) * 2010-12-30 2016-10-04 Rolls-Royce North American Technologies Inc. Compressor tip clearance control and gas turbine engine
US9157331B2 (en) * 2011-12-08 2015-10-13 Siemens Aktiengesellschaft Radial active clearance control for a gas turbine engine
US8967951B2 (en) 2012-01-10 2015-03-03 General Electric Company Turbine assembly and method for supporting turbine components
US9587507B2 (en) 2013-02-23 2017-03-07 Rolls-Royce North American Technologies, Inc. Blade clearance control for gas turbine engine
US9598974B2 (en) 2013-02-25 2017-03-21 Pratt & Whitney Canada Corp. Active turbine or compressor tip clearance control
WO2015094622A1 (fr) 2013-12-17 2015-06-25 United Technologies Corporation Système de commande d'espacement de pale de machine à turbine
US10337353B2 (en) 2014-12-31 2019-07-02 General Electric Company Casing ring assembly with flowpath conduction cut
EP3078811B1 (fr) 2015-04-10 2018-09-26 Rolls-Royce Deutschland Ltd & Co KG Moteur turbo avec un système de protection
US10738791B2 (en) * 2015-12-16 2020-08-11 General Electric Company Active high pressure compressor clearance control
US10247029B2 (en) * 2016-02-04 2019-04-02 United Technologies Corporation Method for clearance control in a gas turbine engine
US10393149B2 (en) * 2016-03-11 2019-08-27 General Electric Company Method and apparatus for active clearance control
US10415420B2 (en) 2016-04-08 2019-09-17 United Technologies Corporation Thermal lifting member for blade outer air seal support
US10612405B2 (en) * 2017-01-13 2020-04-07 United Technologies Corporation Stator outer platform sealing and retainer
US10330009B2 (en) 2017-01-13 2019-06-25 United Technologies Corporation Lock for threaded in place nosecone or spinner
US10344983B2 (en) * 2017-06-20 2019-07-09 Pratt & Whitney Canada Corp. Assembly of tube and structure crossing multi chambers
US10753223B2 (en) 2017-10-04 2020-08-25 General Electric Company Active centering control for static annular turbine flowpath structures
US10704560B2 (en) 2018-06-13 2020-07-07 Rolls-Royce Corporation Passive clearance control for a centrifugal impeller shroud
US11047258B2 (en) 2018-10-18 2021-06-29 Rolls-Royce Plc Turbine assembly with ceramic matrix composite vane components and cooling features
US10927696B2 (en) * 2018-10-19 2021-02-23 Raytheon Technologies Corporation Compressor case clearance control logic
US11015475B2 (en) 2018-12-27 2021-05-25 Rolls-Royce Corporation Passive blade tip clearance control system for gas turbine engine
US11293298B2 (en) 2019-12-05 2022-04-05 Raytheon Technologies Corporation Heat transfer coefficients in a compressor case for improved tip clearance control system

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3085398A (en) * 1961-01-10 1963-04-16 Gen Electric Variable-clearance shroud structure for gas turbine engines
US4242042A (en) * 1978-05-16 1980-12-30 United Technologies Corporation Temperature control of engine case for clearance control
US4247247A (en) * 1979-05-29 1981-01-27 General Motors Corporation Blade tip clearance control
DE2922835C2 (de) * 1979-06-06 1985-06-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Umfangsspaltdichtung an Axialströmungsmaschinen
US4329114A (en) * 1979-07-25 1982-05-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Active clearance control system for a turbomachine
GB2103294B (en) * 1981-07-11 1984-08-30 Rolls Royce Shroud assembly for a gas turbine engine

Also Published As

Publication number Publication date
US4683716A (en) 1987-08-04
GB2169962A (en) 1986-07-23
DE3601546A1 (de) 1986-07-24
JPS61185602A (ja) 1986-08-19
FR2578291A1 (fr) 1986-09-05
GB2169962B (en) 1988-07-13

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Legal Events

Date Code Title Description
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