FR2452600A1 - GAS TURBINE ENGINE WITH LONGITUDINALLY DIVIDED COMPRESSOR HOUSING COMPRISING MANIFOLDS EXTENDING CIRCUMFERENTIALLY AROUND THE HOUSING - Google Patents

GAS TURBINE ENGINE WITH LONGITUDINALLY DIVIDED COMPRESSOR HOUSING COMPRISING MANIFOLDS EXTENDING CIRCUMFERENTIALLY AROUND THE HOUSING

Info

Publication number
FR2452600A1
FR2452600A1 FR8005868A FR8005868A FR2452600A1 FR 2452600 A1 FR2452600 A1 FR 2452600A1 FR 8005868 A FR8005868 A FR 8005868A FR 8005868 A FR8005868 A FR 8005868A FR 2452600 A1 FR2452600 A1 FR 2452600A1
Authority
FR
France
Prior art keywords
housing
gas turbine
turbine engine
crankcase
circumferentially around
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.)
Granted
Application number
FR8005868A
Other languages
French (fr)
Other versions
FR2452600B1 (en
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies 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
Priority claimed from US06/024,635 external-priority patent/US4412782A/en
Priority claimed from US06/024,636 external-priority patent/US4268221A/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of FR2452600A1 publication Critical patent/FR2452600A1/en
Application granted granted Critical
Publication of FR2452600B1 publication Critical patent/FR2452600B1/fr
Granted 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

L'INVENTION CONCERNE UNE STRUCTURE DE COMPRESSEUR CONCUE POUR UN CONTROLE ACTIF DES ESPACES LIBRES. CETTE STRUCTURE COMPREND UN CARTER 16 DIVISE LONGITUDINALEMENT EN DEUX PARTIES ET COMPORTANT UN COLLECTEUR DE PURGE EXTERIEUR 24, 26 A SECTION TRANSVERSALE CIRCULAIRE S'ETENDANT EN TRAVERS DE LA SEPARATION LONGITUDINALE DU CARTER 16. DE L'AIR DE REFROIDISSEMENT PEUT ETRE DECHARGE EN DESSOUS DU COLLECTEUR 24, 26 POUR REFROIDIR LA STRUCTURE DU CARTER 16. L'INVENTION EST UTILISEE POUR CONTROLER LES ESPACES LIBRES DANS UN MOTEUR A TURBINE A GAZ ET REDUIRE AINSI LES DEFORMATIONS THERMIQUES.THE INVENTION RELATES TO A COMPRESSOR STRUCTURE DESIGNED FOR ACTIVE CONTROL OF FREE SPACES. THIS STRUCTURE INCLUDES A CRANKCASE 16 DIVIDED LONGITUDINALLY INTO TWO PARTS AND INCLUDING AN EXTERNAL PURGE MANIFOLD 24, 26 WITH A CIRCULAR CROSS SECTION EXTENDING THROUGH THE LONGITUDINAL SEPARATION OF THE CRANKCASE 16. COOLING AIR CAN BE DISCHARGED FROM THE CRANKCASE 16. MANIFOLD 24, 26 FOR COOLING THE STRUCTURE OF THE CRANKCASE 16. THE INVENTION IS USED TO CONTROL FREE SPACES IN A GAS TURBINE ENGINE AND THUS REDUCE THERMAL DEFORMATION.

FR8005868A 1979-03-28 1980-03-17 GAS TURBINE ENGINE WITH LONGITUDINALLY DIVIDED COMPRESSOR HOUSING COMPRISING MANIFOLDS EXTENDING CIRCUMFERENTIALLY AROUND THE HOUSING Granted FR2452600A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US06/024,635 US4412782A (en) 1979-03-28 1979-03-28 Full hoop bleed manifolds for longitudinally split compressor cases
US06/024,636 US4268221A (en) 1979-03-28 1979-03-28 Compressor structure adapted for active clearance control

Publications (2)

Publication Number Publication Date
FR2452600A1 true FR2452600A1 (en) 1980-10-24
FR2452600B1 FR2452600B1 (en) 1984-05-11

Family

ID=26698681

Family Applications (1)

Application Number Title Priority Date Filing Date
FR8005868A Granted FR2452600A1 (en) 1979-03-28 1980-03-17 GAS TURBINE ENGINE WITH LONGITUDINALLY DIVIDED COMPRESSOR HOUSING COMPRISING MANIFOLDS EXTENDING CIRCUMFERENTIALLY AROUND THE HOUSING

Country Status (3)

Country Link
DE (1) DE3011503A1 (en)
FR (1) FR2452600A1 (en)
GB (1) GB2048386B (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2534982A1 (en) * 1982-10-22 1984-04-27 Snecma Control device for the tolerances of a high-pressure compressor
FR2535795A1 (en) * 1982-11-08 1984-05-11 Snecma AXIS COMPRESSOR STATORIC AUB SUSPENSION DEVICE FOR ACTIVE CONTROL OF GAMES BETWEEN ROTOR AND STATOR
FR2557212A1 (en) * 1983-12-21 1985-06-28 United Technologies Corp STATOR STRUCTURE FOR A GAS TURBINE ENGINE

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8907706D0 (en) * 1989-04-05 1989-05-17 Rolls Royce Plc An axial flow compressor
US5351478A (en) * 1992-05-29 1994-10-04 General Electric Company Compressor casing assembly
US6109868A (en) * 1998-12-07 2000-08-29 General Electric Company Reduced-length high flow interstage air extraction
DE10019437A1 (en) * 2000-04-19 2001-12-20 Rolls Royce Deutschland Method and device for cooling the housings of turbines of jet engines
US7374396B2 (en) * 2005-02-28 2008-05-20 General Electric Company Bolt-on radial bleed manifold
DE102007035927A1 (en) * 2007-07-31 2009-02-05 Mtu Aero Engines Gmbh Control for a gas turbine with actively stabilized compressor
DE102008025511A1 (en) 2008-05-28 2009-12-03 Mtu Aero Engines Gmbh Housing for a compressor of a gas turbine, compressor and method for producing a housing segment of a compressor housing
US9085982B2 (en) 2012-03-19 2015-07-21 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine
DE102013224982A1 (en) * 2013-12-05 2015-06-11 Rolls-Royce Deutschland Ltd & Co Kg Aircraft gas turbine with a core engine housing with cooling air tubes

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3878677A (en) * 1974-04-10 1975-04-22 United Aircraft Corp Auxiliary turbine/compressor system for turbine engine
US4034558A (en) * 1975-10-14 1977-07-12 Westinghouse Canada Limited Cooling apparatus for split shaft gas turbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3878677A (en) * 1974-04-10 1975-04-22 United Aircraft Corp Auxiliary turbine/compressor system for turbine engine
US4034558A (en) * 1975-10-14 1977-07-12 Westinghouse Canada Limited Cooling apparatus for split shaft gas turbine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2534982A1 (en) * 1982-10-22 1984-04-27 Snecma Control device for the tolerances of a high-pressure compressor
FR2535795A1 (en) * 1982-11-08 1984-05-11 Snecma AXIS COMPRESSOR STATORIC AUB SUSPENSION DEVICE FOR ACTIVE CONTROL OF GAMES BETWEEN ROTOR AND STATOR
EP0110757A1 (en) * 1982-11-08 1984-06-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Axial compressor stator blade fixing device for the active control of the play between rotor and stator
US4543039A (en) * 1982-11-08 1985-09-24 Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Stator assembly for an axial compressor
FR2557212A1 (en) * 1983-12-21 1985-06-28 United Technologies Corp STATOR STRUCTURE FOR A GAS TURBINE ENGINE

Also Published As

Publication number Publication date
FR2452600B1 (en) 1984-05-11
GB2048386B (en) 1982-11-24
GB2048386A (en) 1980-12-10
DE3011503A1 (en) 1980-10-09

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Legal Events

Date Code Title Description
ST Notification of lapse