FR2452600A1 - Moteur a turbine a gaz avec un carter de compresseur divise longitudinalement et comportant des collecteurs s'etendant circonferentiellement autour du carter - Google Patents

Moteur a turbine a gaz avec un carter de compresseur divise longitudinalement et comportant des collecteurs s'etendant circonferentiellement autour du carter

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
English (en)
French (fr)
Other versions
FR2452600B1 (https=
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.)
RTX 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/fr
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

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)
  • Compressor (AREA)
FR8005868A 1979-03-28 1980-03-17 Moteur a turbine a gaz avec un carter de compresseur divise longitudinalement et comportant des collecteurs s'etendant circonferentiellement autour du carter Granted FR2452600A1 (fr)

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 (fr) 1980-10-24
FR2452600B1 FR2452600B1 (https=) 1984-05-11

Family

ID=26698681

Family Applications (1)

Application Number Title Priority Date Filing Date
FR8005868A Granted FR2452600A1 (fr) 1979-03-28 1980-03-17 Moteur a turbine a gaz avec un carter de compresseur divise longitudinalement et comportant des collecteurs s'etendant circonferentiellement autour du carter

Country Status (3)

Country Link
DE (1) DE3011503A1 (https=)
FR (1) FR2452600A1 (https=)
GB (1) GB2048386B (https=)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2534982A1 (fr) * 1982-10-22 1984-04-27 Snecma Dispositif de controle des jeux d'un compresseur haute pression
FR2535795A1 (fr) * 1982-11-08 1984-05-11 Snecma Dispositif de suspension d'aubes statoriques de compresseur axial pour le controle actif des jeux entre rotor et stator
FR2557212A1 (fr) * 1983-12-21 1985-06-28 United Technologies Corp Structure de stator pour un moteur a turbine a gaz

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 (de) * 2000-04-19 2001-12-20 Rolls Royce Deutschland Verfahren und Vorrichtung zum Kühlen der Gehäuse von Turbinen von Strahltriebwerken
US7374396B2 (en) * 2005-02-28 2008-05-20 General Electric Company Bolt-on radial bleed manifold
DE102007035927A1 (de) * 2007-07-31 2009-02-05 Mtu Aero Engines Gmbh Regelung für eine Gasturbine mit aktiv stabilisiertem Verdichter
DE102008025511A1 (de) * 2008-05-28 2009-12-03 Mtu Aero Engines Gmbh Gehäuse für einen Verdichter einer Gasturbine, Verdichter und Verfahren zur Herstellung eines Gehäusesegments eines Verdichtergehäuses
US9085982B2 (en) 2012-03-19 2015-07-21 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine
DE102013224982A1 (de) * 2013-12-05 2015-06-11 Rolls-Royce Deutschland Ltd & Co Kg Fluggasturbine mit einem Kern-Triebwerksgehäuse mit Kühlluftröhren

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 (fr) * 1982-10-22 1984-04-27 Snecma Dispositif de controle des jeux d'un compresseur haute pression
FR2535795A1 (fr) * 1982-11-08 1984-05-11 Snecma Dispositif de suspension d'aubes statoriques de compresseur axial pour le controle actif des jeux entre rotor et stator
EP0110757A1 (fr) * 1982-11-08 1984-06-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif de suspension d'aubes statoriques de compresseur axial pour le contrôle actif des jeux entre rotor et 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 (fr) * 1983-12-21 1985-06-28 United Technologies Corp Structure de stator pour un moteur a turbine a gaz

Also Published As

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

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JPH0357298B2 (https=)

Legal Events

Date Code Title Description
ST Notification of lapse