GB870182A - Air inlet for high speed aircraft - Google Patents

Air inlet for high speed aircraft

Info

Publication number
GB870182A
GB870182A GB30591/58A GB3059158A GB870182A GB 870182 A GB870182 A GB 870182A GB 30591/58 A GB30591/58 A GB 30591/58A GB 3059158 A GB3059158 A GB 3059158A GB 870182 A GB870182 A GB 870182A
Authority
GB
United Kingdom
Prior art keywords
air
intake
cowl
aircraft
high speed
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
GB30591/58A
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.)
RTX Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB870182A publication Critical patent/GB870182A/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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

870,182. Air intakes for aircraft. UNITED AIRCRAFT CORPORATION. Sept. 24, 1958 [Dec. 23, 1957], No. 30591/58. Class 4. [Also in Group XXVI] An air intake for the power plant of a high speed aircraft (described in the embodiment in terms of a wind tunnel model) comprises an upstream opening 20 which passes air to a supersonic diffuser portion 22 and thence through a throat 24 to a subsonic diffuser 26. The intake is formed by a compression surface 28 which is part-circular in cross-section and forms the major, fixed portion of the intake and by a slidable cowl 30 which is positioned by a further outer fixed wall 50 for longitudinal sliding movement to vary the geometry of the leading edge of the air intake. A screwjack mechanism 60, 62 enclosed in a fairing 74 and operated by a motor 68, effects axial movement of cowl 30. Boundary layer air on surface 28 is bled off by a scoop 38 which exhausts through a passage 40 and boundary layer bleed passages 34, 32 are formed in surface 28 and cowl 30 respectively.
GB30591/58A 1957-12-23 1958-09-24 Air inlet for high speed aircraft Expired GB870182A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US870182XA 1957-12-23 1957-12-23

Publications (1)

Publication Number Publication Date
GB870182A true GB870182A (en) 1961-06-14

Family

ID=22202484

Family Applications (1)

Application Number Title Priority Date Filing Date
GB30591/58A Expired GB870182A (en) 1957-12-23 1958-09-24 Air inlet for high speed aircraft

Country Status (1)

Country Link
GB (1) GB870182A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4477039A (en) * 1982-06-30 1984-10-16 Mcdonnell Douglas Corporation Vented cowl variable geometry inlet for aircraft
US5004187A (en) * 1988-08-04 1991-04-02 Office National D'etudes Et De Recherches Aerospatiales Symmetrical, two dimensional, supersonic and hypersonic air intake for the combustion air of an aircraft engine
GB2243190A (en) * 1990-03-19 1991-10-23 Gen Electric Ejecting foreign matter from the primary flow path of a gas turbine engine
FR2824106A1 (en) * 2001-04-30 2002-10-31 Aerospatiale Matra Missiles AIR HANDLE AND FLYING MACHINE, ESPECIALLY A MISSILE, PROVIDED WITH SUCH AN AIR HANDLE
US9890711B2 (en) 2010-09-21 2018-02-13 United Technologies Corporation Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4477039A (en) * 1982-06-30 1984-10-16 Mcdonnell Douglas Corporation Vented cowl variable geometry inlet for aircraft
US5004187A (en) * 1988-08-04 1991-04-02 Office National D'etudes Et De Recherches Aerospatiales Symmetrical, two dimensional, supersonic and hypersonic air intake for the combustion air of an aircraft engine
GB2243190A (en) * 1990-03-19 1991-10-23 Gen Electric Ejecting foreign matter from the primary flow path of a gas turbine engine
US5123240A (en) * 1990-03-19 1992-06-23 General Electric Co. Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine
GB2243190B (en) * 1990-03-19 1994-04-13 Gen Electric Apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine.
FR2824106A1 (en) * 2001-04-30 2002-10-31 Aerospatiale Matra Missiles AIR HANDLE AND FLYING MACHINE, ESPECIALLY A MISSILE, PROVIDED WITH SUCH AN AIR HANDLE
EP1255032A1 (en) * 2001-04-30 2002-11-06 Mbdam Air intake and flying vehicle, in particular a missile, with such air intake
US6575404B2 (en) 2001-04-30 2003-06-10 Medam F Air intake and flying device, particularly a missile, equipped with such an air intake
US9890711B2 (en) 2010-09-21 2018-02-13 United Technologies Corporation Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events

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