GB1314162A - Intake anti-icing system for gas turbine engines - Google Patents

Intake anti-icing system for gas turbine engines

Info

Publication number
GB1314162A
GB1314162A GB1314162DA GB1314162A GB 1314162 A GB1314162 A GB 1314162A GB 1314162D A GB1314162D A GB 1314162DA GB 1314162 A GB1314162 A GB 1314162A
Authority
GB
United Kingdom
Prior art keywords
cone
rotor
nose
compressor
generator
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
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
Publication of GB1314162A publication Critical patent/GB1314162A/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
    • F02C7/047—Heating to prevent icing

Abstract

1314162 Permanent magnet generators; two-part couplings DEFENCE SECRETARY OF STATE FOR 24 July 1970 [8 May 1969] 23488/69 Headings H2A and H2E [Also in Divisions F1 and H5] A nose cone 10 at the intake to the compressor of a gas turbine engine is constructed such that when the nose cone is assembled into the engine an electrical connection to heating means 20 on the cone is automatically made. The heating means 20 is for de-icing and comprises a rubber mat bonded to the interior surface 22 of the cone 10 or spirally wound conductors brazed into grooves, the turns being closer together at the cone front. Current is supplied to the heater 20 by a generator having a rotor 16 surrounding a stator 18. The latter consists of permanent magnets held by pins in a housing 24 inwards of compressor stator blades 14. The rotor 16 is a wound armature supported from the compressor rotor 12 by a titanium structure 11, leakage air 40 cools the generator. The three phase A.C. output is tapped from armature 16 through three angularly spaced conductors 26 each of which has rubber sheathing 28 supported in a titanium conduit 30. The forward end of each conductor 26 carries a plug 34 and a ceramic insulator 32. The nose-cone 10 carries corresponding sockets 36 connected to heater 20 and each including an insulator 38 and a leaf spring (39, Fig. 3, not shown). Thus when the nose-cone 10 is moved axially into its assembled portion on the compressor rotor 12 plugs 34 enter sockets 36 to automatically make the electrical connection to heaters 20. The cone is then secured in position by bolts 37. In a modification, when the cone is a stationary member the generator stator is supported by inlet guide vanes upstream of rotor stage 12.
GB1314162D 1969-05-08 1969-05-08 Intake anti-icing system for gas turbine engines Expired GB1314162A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2348869 1969-05-08

Publications (1)

Publication Number Publication Date
GB1314162A true GB1314162A (en) 1973-04-18

Family

ID=10196426

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1314162D Expired GB1314162A (en) 1969-05-08 1969-05-08 Intake anti-icing system for gas turbine engines

Country Status (1)

Country Link
GB (1) GB1314162A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1715160A1 (en) * 2005-04-22 2006-10-25 Rohr, Inc. Aircraft engine nacelle inlet having electrical ice protection system
FR2898869A1 (en) * 2006-03-24 2007-09-28 Aircelle Sa Turbo jet engine nacelle`s air inlet lip for collecting air, has electric heating element providing deicing function, and electric connector connected to electric supply connector for receiving conductive cap to ensure electric continuity
US7469862B2 (en) 2005-04-22 2008-12-30 Goodrich Corporation Aircraft engine nacelle inlet having access opening for electrical ice protection system
US7832983B2 (en) 2006-05-02 2010-11-16 Goodrich Corporation Nacelles and nacelle components containing nanoreinforced carbon fiber composite material
GB2500454A (en) * 2012-03-21 2013-09-25 Mitsui Shipbuilding Eng Gas turbine intake anti-icing device
US8561934B2 (en) 2009-08-28 2013-10-22 Teresa M. Kruckenberg Lightning strike protection
US8752279B2 (en) 2007-01-04 2014-06-17 Goodrich Corporation Methods of protecting an aircraft component from ice formation
US8962130B2 (en) 2006-03-10 2015-02-24 Rohr, Inc. Low density lightning strike protection for use in airplanes

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7681838B2 (en) 2005-04-22 2010-03-23 Rohr, Inc. Aircraft engine nacelle inlet having access opening for electrical ice protection system
EP1715160A1 (en) * 2005-04-22 2006-10-25 Rohr, Inc. Aircraft engine nacelle inlet having electrical ice protection system
US7631838B2 (en) 2005-04-22 2009-12-15 Rohr, Inc. Aircraft engine nacelle inlet having access opening for electrical ice protection system
US7469862B2 (en) 2005-04-22 2008-12-30 Goodrich Corporation Aircraft engine nacelle inlet having access opening for electrical ice protection system
US7513458B2 (en) 2005-04-22 2009-04-07 Rohr, Inc. Aircraft engine nacelle inlet having electrical ice protection system
US8962130B2 (en) 2006-03-10 2015-02-24 Rohr, Inc. Low density lightning strike protection for use in airplanes
WO2007122307A1 (en) * 2006-03-24 2007-11-01 Aircelle Air inlet lip for a pod with electric defrosting
FR2898869A1 (en) * 2006-03-24 2007-09-28 Aircelle Sa Turbo jet engine nacelle`s air inlet lip for collecting air, has electric heating element providing deicing function, and electric connector connected to electric supply connector for receiving conductive cap to ensure electric continuity
US8540185B2 (en) 2006-03-24 2013-09-24 Aircelle Modular air inlet lip with electric defrosting for a turbojet pod
CN101415607B (en) * 2006-03-24 2012-05-23 埃尔塞乐公司 Air inlet lip for a pod with electric defrosting
US7832983B2 (en) 2006-05-02 2010-11-16 Goodrich Corporation Nacelles and nacelle components containing nanoreinforced carbon fiber composite material
US8752279B2 (en) 2007-01-04 2014-06-17 Goodrich Corporation Methods of protecting an aircraft component from ice formation
US8561934B2 (en) 2009-08-28 2013-10-22 Teresa M. Kruckenberg Lightning strike protection
GB2500454A (en) * 2012-03-21 2013-09-25 Mitsui Shipbuilding Eng Gas turbine intake anti-icing device

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees