FR2431609A1 - Systeme d'alimentation en air de refroidissement pour moteur a turbine a gaz - Google Patents

Systeme d'alimentation en air de refroidissement pour moteur a turbine a gaz

Info

Publication number
FR2431609A1
FR2431609A1 FR7918427A FR7918427A FR2431609A1 FR 2431609 A1 FR2431609 A1 FR 2431609A1 FR 7918427 A FR7918427 A FR 7918427A FR 7918427 A FR7918427 A FR 7918427A FR 2431609 A1 FR2431609 A1 FR 2431609A1
Authority
FR
France
Prior art keywords
source
air
air supply
gas turbine
supply system
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
FR7918427A
Other languages
English (en)
Other versions
FR2431609B1 (fr
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
Publication of FR2431609A1 publication Critical patent/FR2431609A1/fr
Application granted granted Critical
Publication of FR2431609B1 publication Critical patent/FR2431609B1/fr
Expired 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
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Valve Device For Special Equipments (AREA)

Abstract

Système réduisant au maximum le jeu rotor/virole aussi bien en régime permanent qu'en régime transitoire. Il comprend : a. une premiere et une seconde source d'air, la température de cette seconde source d'air étant plus élevée que celle de cette première source; b. une première et une seconde vanne d'air 55, 60, destinées à régler l'écoulement d'air venant respectivement de la première et de la seconde source en arrivant dans un collecteur; c. un dispositif qui alimente le support en air venant du collecteur; et d. un servodistributeur 48, sensible à la vitesse du rotor et au temps écoulé après atteinte par le rotor de vitesses prédéterminées, qui fait fonctionner la première et la seconde vanne. Application aux moteurs d'avion.
FR7918427A 1978-07-17 1979-07-17 Systeme d'alimentation en air de refroidissement pour moteur a turbine a gaz Expired FR2431609B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/925,353 US4230439A (en) 1978-07-17 1978-07-17 Air delivery system for regulating thermal growth

Publications (2)

Publication Number Publication Date
FR2431609A1 true FR2431609A1 (fr) 1980-02-15
FR2431609B1 FR2431609B1 (fr) 1986-07-11

Family

ID=25451607

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7918427A Expired FR2431609B1 (fr) 1978-07-17 1979-07-17 Systeme d'alimentation en air de refroidissement pour moteur a turbine a gaz

Country Status (7)

Country Link
US (1) US4230439A (fr)
JP (1) JPS5537594A (fr)
CA (1) CA1119524A (fr)
DE (1) DE2927760A1 (fr)
FR (1) FR2431609B1 (fr)
GB (1) GB2025537B (fr)
IT (1) IT1125410B (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4849895A (en) * 1987-04-15 1989-07-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) System for adjusting radial clearance between rotor and stator elements

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4338061A (en) * 1980-06-26 1982-07-06 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Control means for a gas turbine engine
US4391290A (en) * 1980-10-23 1983-07-05 General Electric Company Altitude sensing control apparatus for a gas turbine engine
GB2108586B (en) * 1981-11-02 1985-08-07 United Technologies Corp Gas turbine engine active clearance control
US4525998A (en) * 1982-08-02 1985-07-02 United Technologies Corporation Clearance control for gas turbine engine
JPS5951105A (ja) * 1982-09-20 1984-03-24 Hitachi Ltd 蒸気タ−ビンの間隙制御方法
US4632635A (en) * 1984-12-24 1986-12-30 Allied Corporation Turbine blade clearance controller
US4928240A (en) * 1988-02-24 1990-05-22 General Electric Company Active clearance control
US5076050A (en) * 1989-06-23 1991-12-31 United Technologies Corporation Thermal clearance control method for gas turbine engine
US5005352A (en) * 1989-06-23 1991-04-09 United Technologies Corporation Clearance control method for gas turbine engine
FR2652858B1 (fr) * 1989-10-11 1993-05-07 Snecma Stator de turbomachine associe a des moyens de deformation.
DE4327376A1 (de) * 1993-08-14 1995-02-16 Abb Management Ag Verdichter sowie Verfahren zu dessen Betrieb
DE102010020800A1 (de) * 2010-05-18 2011-11-24 Rolls-Royce Deutschland Ltd & Co Kg Verfahren und Vorrichtung zur Kühlluftversorgung für ein Triebwerk, insbesondere Flugtriebwerk, Gasturbine oder dergleichen
EP3040519B1 (fr) 2014-12-16 2017-04-26 Rolls-Royce plc Contrôle du jeu des extrémités d'aubes de turbine
EP3040518B1 (fr) 2014-12-16 2017-04-26 Rolls-Royce plc Contrôle du jeu des extrémités d'aubes de turbine
US20190078459A1 (en) * 2017-09-11 2019-03-14 United Technologies Corporation Active clearance control system for gas turbine engine with power turbine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3453825A (en) * 1966-05-04 1969-07-08 Rolls Royce Gas turbine engine having turbine discs with reduced temperature differential
GB1248198A (en) * 1970-02-06 1971-09-29 Rolls Royce Sealing device
FR2280791A1 (fr) * 1974-07-31 1976-02-27 Snecma Perfectionnements au reglage du jeu entre les aubes et le stator d'une turbine
FR2360750A1 (fr) * 1976-08-02 1978-03-03 Gen Electric Procede pour reduire le jeu fonctionnel entre un rotor de turbine et la frette qui l'entoure

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal
US3575528A (en) * 1968-10-28 1971-04-20 Gen Motors Corp Turbine rotor cooling
US3736069A (en) * 1968-10-28 1973-05-29 Gen Motors Corp Turbine stator cooling control
BE756582A (fr) * 1969-10-02 1971-03-01 Gen Electric Ecran circulaire et support d'ecran avec dispositif de reglage de la temperature pour turbomachine
US3584458A (en) * 1969-11-25 1971-06-15 Gen Motors Corp Turbine cooling
US3966354A (en) * 1974-12-19 1976-06-29 General Electric Company Thermal actuated valve for clearance control
US4069662A (en) * 1975-12-05 1978-01-24 United Technologies Corporation Clearance control for gas turbine engine
US4102595A (en) * 1976-10-19 1978-07-25 General Electric Company Bleed valve control system
US4117669A (en) * 1977-03-04 1978-10-03 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Apparatus and method for reducing thermal stress in a turbine rotor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3453825A (en) * 1966-05-04 1969-07-08 Rolls Royce Gas turbine engine having turbine discs with reduced temperature differential
GB1248198A (en) * 1970-02-06 1971-09-29 Rolls Royce Sealing device
FR2280791A1 (fr) * 1974-07-31 1976-02-27 Snecma Perfectionnements au reglage du jeu entre les aubes et le stator d'une turbine
FR2360750A1 (fr) * 1976-08-02 1978-03-03 Gen Electric Procede pour reduire le jeu fonctionnel entre un rotor de turbine et la frette qui l'entoure

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4849895A (en) * 1987-04-15 1989-07-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) System for adjusting radial clearance between rotor and stator elements

Also Published As

Publication number Publication date
DE2927760A1 (de) 1980-01-31
JPS6316564B2 (fr) 1988-04-09
DE2927760C2 (fr) 1987-05-27
US4230439A (en) 1980-10-28
GB2025537A (en) 1980-01-23
JPS5537594A (en) 1980-03-15
CA1119524A (fr) 1982-03-09
IT1125410B (it) 1986-05-14
IT7923984A0 (it) 1979-06-29
GB2025537B (en) 1983-01-12
FR2431609B1 (fr) 1986-07-11

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