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GB1319849A - Gas turbine jet propulsion engines - Google Patents

Gas turbine jet propulsion engines

Info

Publication number
GB1319849A
GB1319849A GB5381570A GB1319849DA GB1319849A GB 1319849 A GB1319849 A GB 1319849A GB 5381570 A GB5381570 A GB 5381570A GB 1319849D A GB1319849D A GB 1319849DA GB 1319849 A GB1319849 A GB 1319849A
Authority
GB
United Kingdom
Prior art keywords
fan
compressor
turbine
nozzle
air
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
GB5381570A
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.)
SECR DEFENCE
UK Secretary of State for Defence
Original Assignee
SECR DEFENCE
UK Secretary of State for Defence
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 SECR DEFENCE, UK Secretary of State for Defence filed Critical SECR DEFENCE
Publication of GB1319849A publication Critical patent/GB1319849A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F02K3/06—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 front fan
    • 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
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • 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
    • F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component
    • 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
    • F02K3/065—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 front and aft fans
    • 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
    • F02K3/077—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 the plant being of the multiple flow type, i.e. having three or more flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1319849 Gas turbine ducted fan engines DEFENCE SECRETARY OF STATE FOR 9 Nov 1971 [12 Nov 1970] 53815/70 Heading F1J The invention relates to a gas turbine ducted fan engine in which the pitch of the fan blades is variable whereby the fan blades may be moved to a reverse pitch so as to provide reverse thrust, the object of the invention being to ensure air flow to the engine compressor during reverse thrust operation. In Fig.1 the engine comprises a compressor 2 disposed so that its air inlet is rearwardly-facing, combustion equipment 3, an HP turbine 4 driving the compressor through shaft 5, and an LP turbine 6 driving fan 7 through shaft 8 and gearing 9. The pitch of the fan blades 7 is controllable by unit 20. The exhaust gases from the turbine 6 discharge radially outwardly through hollow structs 17 which extend across the fan duct 11, and discharge through a rearwardly-directed nozzle 19. The fan duct is defined by a cowl 10 which provides a forward air intake 12 and a rearward fan propulsion nozzle 14. A portion of the air discharged from the fan is directed by means of splitters 15 into the intake 16 of the compressor 2. In reverse thrust operation air is drawn in through the nozzle 14 and passes through fan duct 11 to the fan which discharges it forwardly through the intake 12; air also passes through the nozzle 14 to the intake 16 of the compressor. Flaps 21 on the nozzle 14 are opened in the reverse thrust mode so as to increase the area of the nozzle for air inflow. An auxiliary air inlet may be provided at 22 for use in the reverse thrust mode. A baffle 23 covered with sound absorbing material is disposed in the fan duct. In Fig. 3 (not shown) the engine comprises LP compressor 41 and HP compressor 43, combustion equipment 3, HP turbine 45 and LP turbine 42, the HP turbine driving the HP compressor through shaft 44, and the LP turbine driving the LP compressor also the fan 7 through shaft 8. The LP compressor is oversized so that part of the air compressed thereby discharges through duct 46 and is used either in a forward thrust nozzle 49 or for blown flaps of an aircraft in which the engine is mounted.
GB5381570A 1970-11-12 1970-11-12 Gas turbine jet propulsion engines Expired GB1319849A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5381570 1970-11-12

Publications (1)

Publication Number Publication Date
GB1319849A true GB1319849A (en) 1973-06-13

Family

ID=10469068

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5381570A Expired GB1319849A (en) 1970-11-12 1970-11-12 Gas turbine jet propulsion engines

Country Status (1)

Country Link
GB (1) GB1319849A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2606081A1 (en) * 1986-10-29 1988-05-06 Snecma PROPULSION ENGINE WITH CONTRAROTATING WORKING TURBINES
FR2669680A1 (en) * 1986-06-21 1992-05-29 British Aerospace PREFERENCES PROVIDED TO GAS TURBINE ENGINES OR THE CONCERNS.
EP3067541A3 (en) * 2015-02-19 2016-12-28 United Technologies Corporation Geared turbine engine
US11225913B2 (en) 2015-02-19 2022-01-18 Raytheon Technologies Corporation Method of providing turbine engines with different thrust ratings
US12352181B2 (en) 2023-01-30 2025-07-08 General Electric Company Turbine airfoils

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2669680A1 (en) * 1986-06-21 1992-05-29 British Aerospace PREFERENCES PROVIDED TO GAS TURBINE ENGINES OR THE CONCERNS.
FR2606081A1 (en) * 1986-10-29 1988-05-06 Snecma PROPULSION ENGINE WITH CONTRAROTATING WORKING TURBINES
EP0270403A1 (en) * 1986-10-29 1988-06-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Propulsion engine with contrarotating power turbines
US4765135A (en) * 1986-10-29 1988-08-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Gas turbine engine
EP3067541A3 (en) * 2015-02-19 2016-12-28 United Technologies Corporation Geared turbine engine
US11225913B2 (en) 2015-02-19 2022-01-18 Raytheon Technologies Corporation Method of providing turbine engines with different thrust ratings
US12352181B2 (en) 2023-01-30 2025-07-08 General Electric Company Turbine airfoils

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Legal Events

Date Code Title Description
CSNS Application of which complete specification have been accepted and published, but patent is not sealed