GB885661A - Intakes for supersonic flow - Google Patents

Intakes for supersonic flow

Info

Publication number
GB885661A
GB885661A GB2109159A GB2109159A GB885661A GB 885661 A GB885661 A GB 885661A GB 2109159 A GB2109159 A GB 2109159A GB 2109159 A GB2109159 A GB 2109159A GB 885661 A GB885661 A GB 885661A
Authority
GB
United Kingdom
Prior art keywords
passage
boundary layer
shock wave
engine
throat
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
GB2109159A
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 GB2109159A priority Critical patent/GB885661A/en
Priority to DE1960P0025139 priority patent/DE1121935B/en
Publication of GB885661A publication Critical patent/GB885661A/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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Characterised By The Charging Evacuation (AREA)

Abstract

885,661. Boundary layer control. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. June 8, 1960 [June 19, 1959], No. 21091/59. Class 4. [Also in Group XXVI] A jet propulsion engine air intake of the internal compression type comprises an annular member 31 which defines a convergent passage 32 leading to a throat 33 and a divergent passage 34. In normal operation, the air flowing at supersonic velocity is subject to compression in the convergent passage 32 and a shock wave is established at S3. The flow is then diffused in the divergent passage 34. The wall of member 31 is forced immediately upstream of the throat with an undercut recess 36 which permits the formation of a vortex bearing. The portion 37 of the rotating air forms a bounding wall for the flow in the intake and reduces the losses and the risk of separation due to the interaction of the shock wave and boundary layer. When the engine is throttled back, the pressure in the passage 34 is increased and this causes the shock wave to move to the position S4. This causes the peripheral portion of the vortex bearing to bulge slightly as at 37a and the compression waves C5 to form. The boundary layer flows through the edge of the normal shock S4 and is diffused in the passage 34. The boundary layer may be bled off and directed through the fan of a by-pass or ducted fan engine, or supplied to the combustion chamber of a ram jet or jettisoned.
GB2109159A 1959-06-19 1959-06-19 Intakes for supersonic flow Expired GB885661A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB2109159A GB885661A (en) 1959-06-19 1959-06-19 Intakes for supersonic flow
DE1960P0025139 DE1121935B (en) 1959-06-19 1960-06-09 Air inlet for flow speeds in the supersonic range

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2109159A GB885661A (en) 1959-06-19 1959-06-19 Intakes for supersonic flow

Publications (1)

Publication Number Publication Date
GB885661A true GB885661A (en) 1961-12-28

Family

ID=10157061

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2109159A Expired GB885661A (en) 1959-06-19 1959-06-19 Intakes for supersonic flow

Country Status (2)

Country Link
DE (1) DE1121935B (en)
GB (1) GB885661A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8550770B2 (en) 2011-05-27 2013-10-08 General Electric Company Supersonic compressor startup support system
US8657571B2 (en) 2010-12-21 2014-02-25 General Electric Company Supersonic compressor rotor and methods for assembling same
US8668446B2 (en) 2010-08-31 2014-03-11 General Electric Company Supersonic compressor rotor and method of assembling same
US8770929B2 (en) 2011-05-27 2014-07-08 General Electric Company Supersonic compressor rotor and method of compressing a fluid
US8827640B2 (en) 2011-03-01 2014-09-09 General Electric Company System and methods of assembling a supersonic compressor rotor including a radial flow channel
US8864454B2 (en) 2010-10-28 2014-10-21 General Electric Company System and method of assembling a supersonic compressor system including a supersonic compressor rotor and a compressor assembly
US9022730B2 (en) 2010-10-08 2015-05-05 General Electric Company Supersonic compressor startup support system
CN108301926A (en) * 2018-01-09 2018-07-20 南京航空航天大学 A kind of hypersonic convex turns round contract air intake duct and its design method
CN114458448A (en) * 2022-01-26 2022-05-10 南京航空航天大学 Self-adaptive suction orifice plate for inhibiting shock wave boundary layer interference

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8668446B2 (en) 2010-08-31 2014-03-11 General Electric Company Supersonic compressor rotor and method of assembling same
US9022730B2 (en) 2010-10-08 2015-05-05 General Electric Company Supersonic compressor startup support system
US8864454B2 (en) 2010-10-28 2014-10-21 General Electric Company System and method of assembling a supersonic compressor system including a supersonic compressor rotor and a compressor assembly
US8657571B2 (en) 2010-12-21 2014-02-25 General Electric Company Supersonic compressor rotor and methods for assembling same
US8827640B2 (en) 2011-03-01 2014-09-09 General Electric Company System and methods of assembling a supersonic compressor rotor including a radial flow channel
US8550770B2 (en) 2011-05-27 2013-10-08 General Electric Company Supersonic compressor startup support system
US8770929B2 (en) 2011-05-27 2014-07-08 General Electric Company Supersonic compressor rotor and method of compressing a fluid
CN108301926A (en) * 2018-01-09 2018-07-20 南京航空航天大学 A kind of hypersonic convex turns round contract air intake duct and its design method
CN108301926B (en) * 2018-01-09 2020-06-09 南京航空航天大学 Hypersonic convex-to-circular inner contraction air inlet channel and design method thereof
CN114458448A (en) * 2022-01-26 2022-05-10 南京航空航天大学 Self-adaptive suction orifice plate for inhibiting shock wave boundary layer interference
CN114458448B (en) * 2022-01-26 2023-05-26 南京航空航天大学 Self-adaptive suction orifice plate for inhibiting shock wave boundary layer interference

Also Published As

Publication number Publication date
DE1121935B (en) 1962-01-11

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