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GB879956A - Intakes for fluid flowing at supersonic velocities - Google Patents

Intakes for fluid flowing at supersonic velocities

Info

Publication number
GB879956A
GB879956A GB28497/58A GB2849758A GB879956A GB 879956 A GB879956 A GB 879956A GB 28497/58 A GB28497/58 A GB 28497/58A GB 2849758 A GB2849758 A GB 2849758A GB 879956 A GB879956 A GB 879956A
Authority
GB
United Kingdom
Prior art keywords
intake
wall
lip portion
shroud
wave
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
GB28497/58A
Inventor
Brian Stapleton Stratford
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 GB28497/58A priority Critical patent/GB879956A/en
Priority to DEP23456A priority patent/DE1112902B/en
Priority to FR804254A priority patent/FR1234559A/en
Publication of GB879956A publication Critical patent/GB879956A/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
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)

Abstract

879,956. Gas-turbine jet-propulsion engines. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. Sept. 2, 1959 [Sept. 4, 1958], No. 28497/58. Class 110 (3). An air intake for aircraft designed for flight at supersonic speed, comprises opposite walls defining an intake mouth, the mouth leading rearwardly through ducting to an air consuming combustion engine, e.g. a ram jet or gasturbine, one wall having a forwardly directed lip portion and the other wall including a member arranged to extend forwardly of the lip portion so shaped that under design operating conditions shock-wave formations therefrom extend towards a focus near the lip portion of the intake, and a shroud supported externally of the intake mouth and extending at a lower incidence to the air flow than the lip portion of the intake to intercept the shock wave arising from the forwardly-directed lip of the intake mouth. An annular intake, Fig. 1, comprises an annular wall 1 having a mouth 1a and a forwardly facing lip portion 1b. A centre body 2 is supported in spaced relation to the wall 1 to form a duct 3 leading to an airconsuming engine. The forward part of the body 2 is profiled to a point 2a and the surface 2b is shaped so as to direct shock waves C arising from the surface to a focus at or near the lip portion 1b. The lip portion 1b gives rise to a shock wave S1 which is a high angle shock wave because of the high incidence of the wall 1. To reduce the losses associated with the shock wave S1 an annular shroud 4 is supported in spaced relation to the wall 1 so that its leading edge intercepts the shock wave S1 and reflects it through the annular space between the shroud 4 and wall 1. The low angle of incidence of the shroud 4 produces a weaker shock wave S2 which results in a reduction in wave drag. The shroud 4 should be made as short as possible to minimize skin friction. The mutually facing surfaces 4b, 1c are profiled to give a compressive convergent portion 5, a parallelsided portion and an expansion divergent portion 6. The faces 1c, 4b thus mutually extinguish the disturbance caused by the other; shock waves produced by the wave 1c being cancelled by the aid of face 4b. The intake is described applied to a conventional gas-turbine engine and to a by-pass engine. The engine may be applied to a rectangular intake.
GB28497/58A 1958-09-04 1958-09-04 Intakes for fluid flowing at supersonic velocities Expired GB879956A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB28497/58A GB879956A (en) 1958-09-04 1958-09-04 Intakes for fluid flowing at supersonic velocities
DEP23456A DE1112902B (en) 1958-09-04 1959-09-02 Air inlet for supersonic flows, especially for aircraft
FR804254A FR1234559A (en) 1958-09-04 1959-09-03 Improvements made to the inlets for fluids flowing at supersonic speeds, in particular to the air inlets for stato and turbo-reactors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB28497/58A GB879956A (en) 1958-09-04 1958-09-04 Intakes for fluid flowing at supersonic velocities

Publications (1)

Publication Number Publication Date
GB879956A true GB879956A (en) 1961-10-11

Family

ID=10276572

Family Applications (1)

Application Number Title Priority Date Filing Date
GB28497/58A Expired GB879956A (en) 1958-09-04 1958-09-04 Intakes for fluid flowing at supersonic velocities

Country Status (3)

Country Link
DE (1) DE1112902B (en)
FR (1) FR1234559A (en)
GB (1) GB879956A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009085380A2 (en) 2007-10-24 2009-07-09 Gulfstream Aerospace Corporation Low shock strength inlet
CN115743566A (en) * 2022-10-20 2023-03-07 江西洪都航空工业集团有限责任公司 Double-channel embedded air inlet channel

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5749542A (en) * 1996-05-28 1998-05-12 Lockheed Martin Corporation Transition shoulder system and method for diverting boundary layer air

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009085380A2 (en) 2007-10-24 2009-07-09 Gulfstream Aerospace Corporation Low shock strength inlet
EP2212532A2 (en) * 2007-10-24 2010-08-04 Gulfstream Aerospace Corporation Low shock strength inlet
EP2215341A2 (en) * 2007-10-24 2010-08-11 Gulfstream Aerospace Corporation Low shock strength propulsion system
EP2215341A4 (en) * 2007-10-24 2012-10-24 Gulfstream Aerospace Corp Low shock strength propulsion system
EP2212532A4 (en) * 2007-10-24 2012-10-24 Gulfstream Aerospace Corp Low shock strength inlet
US8393158B2 (en) 2007-10-24 2013-03-12 Gulfstream Aerospace Corporation Low shock strength inlet
US8739514B2 (en) 2007-10-24 2014-06-03 Gulfstream Aerospace Corporation Low shock strength propulsion system
US8783039B2 (en) 2007-10-24 2014-07-22 Gulfstream Aerospace Corporation Low shock strength propulsion system
US8973370B2 (en) 2007-10-24 2015-03-10 Gulfstream Aerospace Corporation Low shock strength propulsion system
US9027583B2 (en) 2007-10-24 2015-05-12 Gulfstream Aerospace Corporation Low shock strength inlet
CN115743566A (en) * 2022-10-20 2023-03-07 江西洪都航空工业集团有限责任公司 Double-channel embedded air inlet channel

Also Published As

Publication number Publication date
FR1234559A (en) 1960-10-18
DE1112902B (en) 1961-08-17

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