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SE8602031L - AIR GAS TURBINE ENGINE - Google Patents

AIR GAS TURBINE ENGINE

Info

Publication number
SE8602031L
SE8602031L SE8602031A SE8602031A SE8602031L SE 8602031 L SE8602031 L SE 8602031L SE 8602031 A SE8602031 A SE 8602031A SE 8602031 A SE8602031 A SE 8602031A SE 8602031 L SE8602031 L SE 8602031L
Authority
SE
Sweden
Prior art keywords
excess
gas turbine
turbine engine
air gas
pressure ratio
Prior art date
Application number
SE8602031A
Other languages
Unknown language ( )
Swedish (sv)
Other versions
SE8602031D0 (en
Inventor
R A Wall
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of SE8602031D0 publication Critical patent/SE8602031D0/en
Publication of SE8602031L publication Critical patent/SE8602031L/en

Links

Classifications

    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/20—Adaptations of gas-turbine plants for driving vehicles
    • F02C6/206—Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/062—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with aft fan

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
  • Separation By Low-Temperature Treatments (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)

Abstract

A gas turbine engine for an aircraft capable of cruise operation at altitudes in excess of 30,000 feet and at mach numbers in excess of 0.6, comprises a core engine including a compressor 12 which is effective for producing a maximum pressure ratio in excess of 40:1. The engine further comprises a propulsor 20 having an air bypass ratio between 10:1 and 60:1. The engine further comprises means for varying the pressure ratio so that the increase in pressure ratio from take-off to cruise is in excess of 20%. <IMAGE>
SE8602031A 1985-05-03 1986-04-30 AIR GAS TURBINE ENGINE SE8602031L (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US73002385A 1985-05-03 1985-05-03

Publications (2)

Publication Number Publication Date
SE8602031D0 SE8602031D0 (en) 1986-04-30
SE8602031L true SE8602031L (en) 1986-11-04

Family

ID=24933598

Family Applications (1)

Application Number Title Priority Date Filing Date
SE8602031A SE8602031L (en) 1985-05-03 1986-04-30 AIR GAS TURBINE ENGINE

Country Status (7)

Country Link
JP (1) JPS61283755A (en)
CA (1) CA1260277A (en)
DE (1) DE3615006A1 (en)
FR (1) FR2581425A1 (en)
GB (1) GB2174761B (en)
IT (1) IT1191772B (en)
SE (1) SE8602031L (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070260424A1 (en) * 2006-05-05 2007-11-08 Harold Brown Methods and apparatus for estimating engine thrust
US8082727B2 (en) 2008-02-26 2011-12-27 United Technologies Corporation Rear propulsor for a variable cycle gas turbine engine
US8127528B2 (en) 2008-02-26 2012-03-06 United Technologies Corporation Auxiliary propulsor for a variable cycle gas turbine engine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1487324A (en) * 1973-11-15 1977-09-28 Rolls Royce Gas turbine engines
US4502275A (en) * 1983-10-13 1985-03-05 Avco Corporation Compressor air bleed override control system

Also Published As

Publication number Publication date
GB2174761A (en) 1986-11-12
SE8602031D0 (en) 1986-04-30
FR2581425A1 (en) 1986-11-07
JPS61283755A (en) 1986-12-13
IT8620278A1 (en) 1987-10-30
IT1191772B (en) 1988-03-23
IT8620278A0 (en) 1986-04-30
CA1260277A (en) 1989-09-26
GB2174761B (en) 1989-09-06
DE3615006A1 (en) 1986-11-13
GB8609742D0 (en) 1986-05-29

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Legal Events

Date Code Title Description
NAV Patent application has lapsed

Ref document number: 8602031-0

Effective date: 19900517