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GB1328993A - Air intakes for gas turbine engines - Google Patents

Air intakes for gas turbine engines

Info

Publication number
GB1328993A
GB1328993A GB547670A GB1328993DA GB1328993A GB 1328993 A GB1328993 A GB 1328993A GB 547670 A GB547670 A GB 547670A GB 1328993D A GB1328993D A GB 1328993DA GB 1328993 A GB1328993 A GB 1328993A
Authority
GB
United Kingdom
Prior art keywords
outer casing
centre body
gas turbine
leading edge
turbine engines
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
GB547670A
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.)
SECR DEFENCE
UK Secretary of State for Defence
Original Assignee
SECR DEFENCE
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 SECR DEFENCE, UK Secretary of State for Defence filed Critical SECR DEFENCE
Publication of GB1328993A publication Critical patent/GB1328993A/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
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles

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)
  • Filtering Of Dispersed Particles In Gases (AREA)
  • Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
  • Supercharger (AREA)

Abstract

1328993 Gas turbine engines - air intakes DEFENCE SECRETARY OF STATE FOR 23 April 1971 [5 Feb 1970] 5476/70 Heading F1G An air intake for a gas turbine engine comprises an outer casing 14, 15 having a leading edge 16, and a centre body 12 having an upstream end portion which is enlarged, an annular passage 18 being defined between the the centre body and the outer casing into which air flows as indicated by arrows 19. The centre body is of mushroom shape and is supported from the outer casing by struts 17. The outer periphery 22 of the centre body is forward of the leading edge 16 of the outer casing and every point of the periphery lies at a greater distance from the axis 23 than a corresponding point in the same axial plane on the leading edge of the outer casing. The object of the invention is to prevent snow and slush being drawn into the intake passage 18. Means 26 are provided for heating the forward face of the centre body.
GB547670A 1970-02-05 1971-04-23 Air intakes for gas turbine engines Expired GB1328993A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB547670 1970-02-05

Publications (1)

Publication Number Publication Date
GB1328993A true GB1328993A (en) 1973-09-05

Family

ID=9796916

Family Applications (1)

Application Number Title Priority Date Filing Date
GB547670A Expired GB1328993A (en) 1970-02-05 1971-04-23 Air intakes for gas turbine engines

Country Status (4)

Country Link
US (1) US3684857A (en)
DE (1) DE2103035C3 (en)
FR (1) FR2079257B1 (en)
GB (1) GB1328993A (en)

Families Citing this family (49)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2069054B (en) * 1980-02-09 1983-06-02 Rolls Royce Water separator gas turbine engine intake
GB2069053B (en) * 1980-02-09 1983-04-13 Rolls Royce Water separator in gas turbine inlet
WO2006060006A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine non-metallic tailcone
WO2006059974A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
US8152469B2 (en) 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
WO2006060003A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
EP1825112B1 (en) 2004-12-01 2013-10-23 United Technologies Corporation Cantilevered tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
WO2006060010A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Compressor inlet guide vane for tip turbine engine and corresponding control method
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
WO2006059999A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
DE602004031986D1 (en) 2004-12-01 2011-05-05 United Technologies Corp BLOWER TURBINE ROTOR ASSEMBLY FOR A TOP TURBINE ENGINE
WO2006059993A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
WO2006059971A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
US7878762B2 (en) 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
WO2006110122A2 (en) 2004-12-01 2006-10-19 United Technologies Corporation Inflatable bleed valve for a turbine engine and a method of operating therefore
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
EP1828591B1 (en) * 2004-12-01 2010-07-21 United Technologies Corporation Peripheral combustor for tip turbine engine
EP1825111B1 (en) 2004-12-01 2011-08-31 United Technologies Corporation Counter-rotating compressor case for a tip turbine engine
DE602004023769D1 (en) * 2004-12-01 2009-12-03 United Technologies Corp STACKED RINGING COMPONENTS FOR TURBINE ENGINES
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
WO2006059988A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Modular tip turbine engine
WO2006059995A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Gearbox lubrication supply system for a tip turbine engine
WO2006059970A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US7921636B2 (en) * 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
EP1825114B1 (en) * 2004-12-01 2008-08-20 United Technologies Corporation Tip turbine engine with a heat exchanger
WO2006060013A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7937927B2 (en) * 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
EP1828567B1 (en) * 2004-12-01 2011-10-12 United Technologies Corporation Diffuser aspiration for a tip turbine engine
EP1834067B1 (en) 2004-12-01 2008-11-26 United Technologies Corporation Fan blade assembly for a tip turbine engine and method of assembly
WO2006059996A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
DE602004031679D1 (en) 2004-12-01 2011-04-14 United Technologies Corp Regenerative cooling of a guide and blade for a tipturbine engine
DE602004031470D1 (en) * 2004-12-01 2011-03-31 United Technologies Corp TRANSITION CHANNEL WITH MEANS FOR FLOW VECTOR INFLUENCE ON A GAS TURBINE
WO2006110124A2 (en) * 2004-12-01 2006-10-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
WO2006059987A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Particle separator for tip turbine engine
WO2006059986A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
US7690186B2 (en) * 2005-11-09 2010-04-06 Pratt & Whitney Canada Corp. Gas turbine engine including apparatus to transfer power between multiple shafts
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US9857017B2 (en) * 2015-10-30 2018-01-02 Akron Brass Company Debris diverting inlet
CN109339948B (en) * 2018-11-23 2021-01-08 江西洪都航空工业集团有限责任公司 Gas turbine engine air inlet device for bombs
US12326114B2 (en) 2023-08-15 2025-06-10 Rtx Corporation Gas turbine engine with core debris protection

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2791668A (en) * 1951-08-21 1957-05-07 Napier & Son Ltd Electrically heated de-icing or antifreezing apparatus
US3063031A (en) * 1959-12-28 1962-11-06 Gen Motors Corp Electrical aircraft heater
US3534548A (en) * 1969-06-30 1970-10-20 Avco Corp Separator apparatus for engine air inlets

Also Published As

Publication number Publication date
DE2103035B2 (en) 1974-08-01
FR2079257B1 (en) 1975-06-06
DE2103035A1 (en) 1971-08-26
FR2079257A1 (en) 1971-11-12
DE2103035C3 (en) 1975-03-27
US3684857A (en) 1972-08-15

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLE Entries relating assignments, transmissions, licences in the register of patents
PCNP Patent ceased through non-payment of renewal fee