GB1026996A - Supersonic intake for a jet propulsion engine - Google Patents

Supersonic intake for a jet propulsion engine

Info

Publication number
GB1026996A
GB1026996A GB3190164A GB3190164A GB1026996A GB 1026996 A GB1026996 A GB 1026996A GB 3190164 A GB3190164 A GB 3190164A GB 3190164 A GB3190164 A GB 3190164A GB 1026996 A GB1026996 A GB 1026996A
Authority
GB
United Kingdom
Prior art keywords
cylinder
fixed structure
spike
outer casing
upstream end
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
GB3190164A
Inventor
Malcolm Roy Pike
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB3190164A priority Critical patent/GB1026996A/en
Priority to US47249465 priority patent/US3314437A/en
Publication of GB1026996A publication Critical patent/GB1026996A/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
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

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)
  • Characterised By The Charging Evacuation (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

1,026,996. Gas turbine jet propulsion plant. ROLLS-ROYCE, Ltd. Aug. 5, 1964, No. 31901/64. Heading FIG. A supersonic air intake for a jet propulsion engine comprises an outer casing having a fixed structure mounted therein to define with the outer casing an annular air intake, the fixed structure being provided with an axially movable coaxial spike whose maximum diameter is substantially less than that of the portion of the fixed structure adjacent the upstream end of the outer casing, the spike extending upstream of the fixed structure. In one embodiment, Fig. 3, the fixed structure comprises a cylinder 26 open at its upstream end to receive ram air and provided with doors 44 which may be opened to introduce this ram air into the annular air intake formed between the cylinder 26 and an outer casing 25. Centrally mounted within the cylinder 26 by struts 33 is a centrebody 34 which carries a spike 36 slidably mounted in a cylinder to which pressure fluid may be introduced to effect axial movement of the spike. At supersonic speeds, shock waves 42, 43 form across the annular air intake. In a modification, Fig. 2 (not shown), the upstream end of the cylinder of the fixed structure is closed. In both embodiments, a substantially conical flow separation zone is formed by the tip of the spike and the periphery of the upstream end of the cylinder.
GB3190164A 1964-08-05 1964-08-05 Supersonic intake for a jet propulsion engine Expired GB1026996A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB3190164A GB1026996A (en) 1964-08-05 1964-08-05 Supersonic intake for a jet propulsion engine
US47249465 US3314437A (en) 1964-08-05 1965-07-16 Supersonic intake for a jet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3190164A GB1026996A (en) 1964-08-05 1964-08-05 Supersonic intake for a jet propulsion engine

Publications (1)

Publication Number Publication Date
GB1026996A true GB1026996A (en) 1966-04-20

Family

ID=10330085

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3190164A Expired GB1026996A (en) 1964-08-05 1964-08-05 Supersonic intake for a jet propulsion engine

Country Status (2)

Country Link
US (1) US3314437A (en)
GB (1) GB1026996A (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3497163A (en) * 1966-05-24 1970-02-24 George H Wakefield Supersonic aircraft
US4418879A (en) * 1980-12-29 1983-12-06 The Boeing Company Scoop and inlet for auxiliary power units and method
US4817892A (en) * 1986-04-28 1989-04-04 Janeke Charl E Aerospace plane and engine therefor
US5381655A (en) * 1993-05-10 1995-01-17 General Electric Company Admission mixing duct assembly
US8393158B2 (en) * 2007-10-24 2013-03-12 Gulfstream Aerospace Corporation Low shock strength inlet
CN112627981B (en) * 2020-11-18 2022-06-28 南京航空航天大学 Axisymmetric internal parallel type bimodal air inlet channel for RBCC engine and control method

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB709300A (en) * 1951-11-12 1954-05-19 Lucas Industries Ltd Jet-propelled aerial bodies
US3008667A (en) * 1953-03-27 1961-11-14 Frank A Dean Ramjet diffuser
US3028731A (en) * 1955-02-02 1962-04-10 Marquardt Corp Fuel-air ratio controller

Also Published As

Publication number Publication date
US3314437A (en) 1967-04-18

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