GB1479023A - Aircraft engine intakes - Google Patents

Aircraft engine intakes

Info

Publication number
GB1479023A
GB1479023A GB34043/74A GB3404374A GB1479023A GB 1479023 A GB1479023 A GB 1479023A GB 34043/74 A GB34043/74 A GB 34043/74A GB 3404374 A GB3404374 A GB 3404374A GB 1479023 A GB1479023 A GB 1479023A
Authority
GB
United Kingdom
Prior art keywords
wall
boundary layer
flow
upstream
extended position
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
GB34043/74A
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.)
Secretary of State for Defence Canada
UK Secretary of State for Defence
Original Assignee
Secretary of State for Defence Canada
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 Secretary of State for Defence Canada, UK Secretary of State for Defence filed Critical Secretary of State for Defence Canada
Priority to GB34043/74A priority Critical patent/GB1479023A/en
Publication of GB1479023A publication Critical patent/GB1479023A/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
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • 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

1479023 Jet propulsion engine air intakes DEFENCE SECRETARY OF STATE FOR 28 July 1975 [1 Aug 1974] 34043/74 Addition to 1166733 Headings F1G and F1J [Also in Division F2] An aircraft engine intake duct having a wall 15 movable to an extended position, shown, during supersonic operation so as to deflect the boundary layer D from an upstream surface 13 and into a bleed aperture 17, as described in Specification 1166733, is additionally provided with a flow diverter 20 having a mouth partly defined by lip 22 and arranged to divert the boundary layer from the main flow when the wall 15 is retracted for subsonic operation. The diverted flow is directed to the free stream flow at the sides of the intake. The movable wall 15 may have an upstream extending lip (30) Fig. 5, (not shown) a suction chamber and draw-off slot (34, 31 respectively), Fig. 6 (not shown) or through-slots (32, 33) Fig. 7 (not shown) to reduce drag when the wall is in its extended position. Boundary layer velocity may be increased by fluid jets. The upstream portion of ramp 11 may be pivotal. In a further modification Fig. 8, (not shown) diverter 20 and bleed 17 have a common entrance aperture.
GB34043/74A 1975-07-28 1975-07-28 Aircraft engine intakes Expired GB1479023A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB34043/74A GB1479023A (en) 1975-07-28 1975-07-28 Aircraft engine intakes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB34043/74A GB1479023A (en) 1975-07-28 1975-07-28 Aircraft engine intakes

Publications (1)

Publication Number Publication Date
GB1479023A true GB1479023A (en) 1977-07-06

Family

ID=10360658

Family Applications (1)

Application Number Title Priority Date Filing Date
GB34043/74A Expired GB1479023A (en) 1975-07-28 1975-07-28 Aircraft engine intakes

Country Status (1)

Country Link
GB (1) GB1479023A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2405366A1 (en) * 1977-10-05 1979-05-04 Rolls Royce IMPROVEMENTS TO THE FLOW DEVIATION DEVICES
FR2476743A1 (en) * 1980-02-26 1981-08-28 Gen Electric IMPROVED AIR INTAKE CASE FOR GAS TURBINE ENGINE
FR2560291A1 (en) * 1984-02-28 1985-08-30 Messerschmitt Boelkow Blohm DEVICE FOR IMPROVING FLOW CONDITIONS AT AIR INTAKE OF TURBO AIRCRAFT MOUNTED IN AIRCRAFT
US4685942A (en) * 1982-12-27 1987-08-11 General Electric Company Axial flow inlet particle separator
GB2248885A (en) * 1990-08-22 1992-04-22 Rolls Royce Plc Compressor inlet flow control means
GB2251031A (en) * 1990-12-19 1992-06-24 Rolls Royce Plc Cooling air pick up for gas turbine engine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2405366A1 (en) * 1977-10-05 1979-05-04 Rolls Royce IMPROVEMENTS TO THE FLOW DEVIATION DEVICES
FR2476743A1 (en) * 1980-02-26 1981-08-28 Gen Electric IMPROVED AIR INTAKE CASE FOR GAS TURBINE ENGINE
US4685942A (en) * 1982-12-27 1987-08-11 General Electric Company Axial flow inlet particle separator
FR2560291A1 (en) * 1984-02-28 1985-08-30 Messerschmitt Boelkow Blohm DEVICE FOR IMPROVING FLOW CONDITIONS AT AIR INTAKE OF TURBO AIRCRAFT MOUNTED IN AIRCRAFT
GB2155413A (en) * 1984-02-28 1985-09-25 Messerschmitt Boelkow Blohm A mechanism for improving flow conditions at air inlets for gas turbine engines installed in aircraft
GB2248885A (en) * 1990-08-22 1992-04-22 Rolls Royce Plc Compressor inlet flow control means
US5230603A (en) * 1990-08-22 1993-07-27 Rolls Royce Plc Control of flow instabilities in turbomachines
GB2248885B (en) * 1990-08-22 1994-12-21 Rolls Royce Plc Control of flow instabilities in turbomachines
GB2251031A (en) * 1990-12-19 1992-06-24 Rolls Royce Plc Cooling air pick up for gas turbine engine
GB2251031B (en) * 1990-12-19 1995-01-18 Rolls Royce Plc Cooling air pick up

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee