GB1393651A - Gas turbine engines having cooled variable guide vane apparatus - Google Patents

Gas turbine engines having cooled variable guide vane apparatus

Info

Publication number
GB1393651A
GB1393651A GB2659373A GB2659373A GB1393651A GB 1393651 A GB1393651 A GB 1393651A GB 2659373 A GB2659373 A GB 2659373A GB 2659373 A GB2659373 A GB 2659373A GB 1393651 A GB1393651 A GB 1393651A
Authority
GB
United Kingdom
Prior art keywords
air
gas turbine
compressor
guide vanes
chamber
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
Application number
GB2659373A
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.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of GB1393651A publication Critical patent/GB1393651A/en
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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)

Abstract

1393651 Gas turbine engines-cooling MOTOREN-UND TURBINEN-UNION MUNCHEN GmbH 4 June 1973 [7 June 1972] 26593/73 Headings F1G and F1T The invention relates to a gas turbine engine comprising variable turbine inlet guide vanes in which a portion of air from the compressor is utilized to cool the variable guide vanes. The gas turbine engine comprises an air compressor 1, a heat exchanger 2, combustion chamber 3 and a turbine 4, the exhaust gases from the turbine discharging through the heat exchanger. The portion of air taken from the compressor for cooling the inlet guide vanes is thereafter mixed with the air discharging from the heat exchanger. The guide vanes 5 are mounted on stems 6 which are angularly movable by mechanism 7, the stems being disposed within a chamber 8. Cooling air from the compressor passes to an annular chamber 10 thence through openings 21 to a chamber 13 and from there through a nozzle 14 on to the guide vane stem and around the mechanism 7; the air then discharges through outlet 15.
GB2659373A 1972-06-07 1973-06-04 Gas turbine engines having cooled variable guide vane apparatus Expired GB1393651A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2227562A DE2227562A1 (en) 1972-06-07 1972-06-07 DEVICE FOR COOLING ADJUSTABLE DIRECTIONAL DEVICES OF GAS TURBINES

Publications (1)

Publication Number Publication Date
GB1393651A true GB1393651A (en) 1975-05-07

Family

ID=5846982

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2659373A Expired GB1393651A (en) 1972-06-07 1973-06-04 Gas turbine engines having cooled variable guide vane apparatus

Country Status (3)

Country Link
DE (1) DE2227562A1 (en)
FR (1) FR2188057A1 (en)
GB (1) GB1393651A (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3516685A1 (en) * 1985-05-09 1986-11-13 Daimler-Benz Ag, 7000 Stuttgart Device for cooling the wire bearing of an air blade adjusting device of a gas turbine

Also Published As

Publication number Publication date
DE2227562A1 (en) 1973-12-20
FR2188057A1 (en) 1974-01-18

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees