GB1298069A - Air intake for a gas turbine engine - Google Patents

Air intake for a gas turbine engine

Info

Publication number
GB1298069A
GB1298069A GB2266969A GB2266969A GB1298069A GB 1298069 A GB1298069 A GB 1298069A GB 2266969 A GB2266969 A GB 2266969A GB 2266969 A GB2266969 A GB 2266969A GB 1298069 A GB1298069 A GB 1298069A
Authority
GB
United Kingdom
Prior art keywords
fan
aperture
intake
air
gas turbine
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
GB2266969A
Inventor
Charles Robert Palmer
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.)
UK Secretary of State for Defence
Original Assignee
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 UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Priority to GB2266969A priority Critical patent/GB1298069A/en
Publication of GB1298069A publication Critical patent/GB1298069A/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
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1298069 Gas turbine engines; air intakes DEFENCE SECRETARY OF STATE FOR 26 May 1970 [3 May 1969] 22669/69 Headings F1G F1J] The invention relates to air intake ducts for gas turbine engines and is described with reference to the fan duct 24 of a gas turbine ducted fan engine which comprises a fan 16 disposed within a duct defined by a double-walled casing 20. The inner wall of the fan casing is formed with a first, upstream aperture 34 and a second, downstream aperture 36, the aperture being inter-connected so as to permit a recirculatory flow or air from aperture to aperture in a downstream direction through the fan duct and in an upstream direction between the walls of the fan casing. In the embodiment the apertures 34, 36 are annular and a chamber 40 is defined between the walls of the casing by a bulkhead 38. Air under pressure is tapped from the engine compressor 12 and discharged through an ejector nozzle into the chamber 40 thus promoting the recirculatory air-flow indicated by the arrows 46. The system is not operative during normal aircraft flight when the effective intake diameter is as indicated at a. At landing the system is operative and the effective diameter of the intake is as indicated at b thus causing "choking" of the intake throat with intake flow velocity approaching sonic whereby passage of noise out of the intake is effectively reduced. Doors may be provided so as to cover the apertures 34, 36 when the system is inoperative. The aperture 36 may alternatively be located at position 50 downstream of fan 16 so that air pressurized by the fan passes into the chamber 40 to cause the re-circulatory flow.
GB2266969A 1969-05-03 1969-05-03 Air intake for a gas turbine engine Expired GB1298069A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2266969A GB1298069A (en) 1969-05-03 1969-05-03 Air intake for a gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2266969A GB1298069A (en) 1969-05-03 1969-05-03 Air intake for a gas turbine engine

Publications (1)

Publication Number Publication Date
GB1298069A true GB1298069A (en) 1972-11-29

Family

ID=10183182

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2266969A Expired GB1298069A (en) 1969-05-03 1969-05-03 Air intake for a gas turbine engine

Country Status (1)

Country Link
GB (1) GB1298069A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2173861A (en) * 1985-04-22 1986-10-22 Gen Electric Directing air flow to an airstream probe
EP1115967A2 (en) * 1998-09-24 2001-07-18 Virginia Tech Intellectual Properties, Inc. Fan noise reduction from turbofan engines using adaptive herschel-quincke tubes
JP2004084669A (en) * 2002-08-27 2004-03-18 General Electric Co <Ge> System and method for actively changing effective flow-through area of intake part region of aircraft engine
US7047725B2 (en) 2003-05-28 2006-05-23 Rohr, Inc. Assembly and method for aircraft engine noise reduction
US7055648B2 (en) 2000-10-02 2006-06-06 Rohr, Inc. Assembly and method for fan noise reduction from turbofan engines using dynamically adaptive Herschel-Quincke tubes
US7297530B2 (en) * 2004-04-01 2007-11-20 Biotrace Limited Device for use in monitoring a swab technique
EP1517022A3 (en) * 2003-09-22 2012-06-13 General Electric Company Method and system for reduction of jet engine noise
FR2970465A1 (en) * 2011-01-19 2012-07-20 Aircelle Sa NACELLE FOR A DOUBLE FLOW AIRCRAFT AIRCRAFT TURBOREACTOR.

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2173861B (en) * 1985-04-22 1989-12-28 Gen Electric Airstream eductor
GB2173861A (en) * 1985-04-22 1986-10-22 Gen Electric Directing air flow to an airstream probe
EP1115967A2 (en) * 1998-09-24 2001-07-18 Virginia Tech Intellectual Properties, Inc. Fan noise reduction from turbofan engines using adaptive herschel-quincke tubes
EP1115967A4 (en) * 1998-09-24 2004-07-28 Virginia Tech Intell Prop Fan noise reduction from turbofan engines using adaptive herschel-quincke tubes
US7055648B2 (en) 2000-10-02 2006-06-06 Rohr, Inc. Assembly and method for fan noise reduction from turbofan engines using dynamically adaptive Herschel-Quincke tubes
US7416051B2 (en) 2000-10-02 2008-08-26 Rohr, Inc. Assembly and method for fan noise reduction from turbofan engines using dynamically adaptive Herschel-Quincke tubes
JP2004084669A (en) * 2002-08-27 2004-03-18 General Electric Co <Ge> System and method for actively changing effective flow-through area of intake part region of aircraft engine
EP1394388A3 (en) * 2002-08-27 2006-07-05 General Electric Company System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine
US7047725B2 (en) 2003-05-28 2006-05-23 Rohr, Inc. Assembly and method for aircraft engine noise reduction
EP1517022A3 (en) * 2003-09-22 2012-06-13 General Electric Company Method and system for reduction of jet engine noise
US7297530B2 (en) * 2004-04-01 2007-11-20 Biotrace Limited Device for use in monitoring a swab technique
FR2970465A1 (en) * 2011-01-19 2012-07-20 Aircelle Sa NACELLE FOR A DOUBLE FLOW AIRCRAFT AIRCRAFT TURBOREACTOR.
FR2970466A1 (en) * 2011-01-19 2012-07-20 Aircelle Sa NACELLE FOR A DOUBLE FLOW AIRCRAFT AIRCRAFT
WO2012098321A2 (en) 2011-01-19 2012-07-26 Aircelle Nacelle for an aircraft bypass turbojet engine
WO2012098322A3 (en) * 2011-01-19 2012-09-13 Aircelle Nacelle for an aircraft bypass turbojet engine
WO2012098321A3 (en) * 2011-01-19 2012-09-13 Aircelle Nacelle for an aircraft bypass turbojet engine
CN103314206A (en) * 2011-01-19 2013-09-18 埃尔塞乐公司 Nacelle for an aircraft bypass turbojet engine
CN103328800A (en) * 2011-01-19 2013-09-25 埃尔塞乐公司 Nacelle for an aircraft bypass turbojet engine

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee