GB743598A - Aircraft boundary layer suction systems and compressors therefor - Google Patents

Aircraft boundary layer suction systems and compressors therefor

Info

Publication number
GB743598A
GB743598A GB10351/53A GB1035153A GB743598A GB 743598 A GB743598 A GB 743598A GB 10351/53 A GB10351/53 A GB 10351/53A GB 1035153 A GB1035153 A GB 1035153A GB 743598 A GB743598 A GB 743598A
Authority
GB
United Kingdom
Prior art keywords
compressor
suction
wing
stages
boundary layer
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
GB10351/53A
Inventor
Alun Raymond Howell
Ivor Macaulay Davidson
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development Ltd
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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB10351/53A priority Critical patent/GB743598A/en
Publication of GB743598A publication Critical patent/GB743598A/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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/04—Boundary layer controls by actively generating fluid flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/22—Boundary layer controls by using a surface having multiple apertures of relatively small openings other than slots
    • 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
    • Y02T50/10—Drag reduction

Abstract

743,598. Controlling boundary layer. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. April 2, 1954 [April 15, 1953], No. 10351/53. Class 4. [Also in Group XXVI] An aircraft boundary layer suction system in which a different degree of suction is to be applied at each of a plurality of suction openings in the surface of the aircraft, comprises a compressor system having a plurality of compression stages arranged for series flow, an inlet to its first stage and further inlets each leading directly to one of its subsequent stages, said suction openings each being connected to a different one of said inlets. The wing comprises areas of porous skin 11, 12, 13, 14 communicating with cells or compartments 15, 16, 17, 18 having conduits 19, 20, 21, 22 connected to the inlet sides of different stages of an axial flow compressor 27 (see Group XXVI) whereby the area 12 subjected to highest pressure is connected to the low-pressure stage of the compressor, the remaining areas being connected in order of decreasing pressure with the successive stages of the compressor. A turbine 29 is drivingly connected to the shaft 28 of the compressor and it is connected by a conduit 76 and a valve 78 to the outlet side of a gas turbine engine 75. The valve 78 is coupled to mechanism 79a according to Specification 606,176, [Group XXVI], for reducing the area of the nozzle of the gas turbine when the turbine 29 is being driven. In a wing having two gas-turbine engines a further compressor may be connected to conduits 65, 66, 67, 68. A further embodiment is described in which the conduits from the wing are connected to the inlets of different stages of a multi-stage centrifugal compressor. An embodiment is described in which suction is applied to the surfaces of a thick section wing having a concave upper surface at the trailing edge.
GB10351/53A 1953-04-15 1953-04-15 Aircraft boundary layer suction systems and compressors therefor Expired GB743598A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB10351/53A GB743598A (en) 1953-04-15 1953-04-15 Aircraft boundary layer suction systems and compressors therefor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB10351/53A GB743598A (en) 1953-04-15 1953-04-15 Aircraft boundary layer suction systems and compressors therefor

Publications (1)

Publication Number Publication Date
GB743598A true GB743598A (en) 1956-01-18

Family

ID=9966249

Family Applications (1)

Application Number Title Priority Date Filing Date
GB10351/53A Expired GB743598A (en) 1953-04-15 1953-04-15 Aircraft boundary layer suction systems and compressors therefor

Country Status (1)

Country Link
GB (1) GB743598A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2886264A (en) * 1957-05-17 1959-05-12 Lockheed Aircraft Corp Stall roll control device for vertical take-off airplane
US3951360A (en) * 1973-07-05 1976-04-20 Rene Anxionnaz Device for regulating and recovering the boundary layer over the surface of a body such as an aircraft in flight
GB2242235A (en) * 1990-03-06 1991-09-25 Gen Electric Aircraft engine bleed system
EP0459815A1 (en) * 1990-06-01 1991-12-04 General Electric Company Gas turbine engine fan duct base pressure drag reduction
US5114103A (en) * 1990-08-27 1992-05-19 General Electric Company Aircraft engine electrically powered boundary layer bleed system
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed
GB2256253A (en) * 1991-05-30 1992-12-02 Short Brothers Plc Boundary layer control.

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2886264A (en) * 1957-05-17 1959-05-12 Lockheed Aircraft Corp Stall roll control device for vertical take-off airplane
US3951360A (en) * 1973-07-05 1976-04-20 Rene Anxionnaz Device for regulating and recovering the boundary layer over the surface of a body such as an aircraft in flight
GB2242235A (en) * 1990-03-06 1991-09-25 Gen Electric Aircraft engine bleed system
EP0459815A1 (en) * 1990-06-01 1991-12-04 General Electric Company Gas turbine engine fan duct base pressure drag reduction
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5141182A (en) * 1990-06-01 1992-08-25 General Electric Company Gas turbine engine fan duct base pressure drag reduction
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed
US5114103A (en) * 1990-08-27 1992-05-19 General Electric Company Aircraft engine electrically powered boundary layer bleed system
GB2256253A (en) * 1991-05-30 1992-12-02 Short Brothers Plc Boundary layer control.
GB2256253B (en) * 1991-05-30 1995-01-11 Short Brothers Plc Boundary layer control
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus

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