GB1210202A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
GB1210202A
GB1210202A GB1197769A GB1197769A GB1210202A GB 1210202 A GB1210202 A GB 1210202A GB 1197769 A GB1197769 A GB 1197769A GB 1197769 A GB1197769 A GB 1197769A GB 1210202 A GB1210202 A GB 1210202A
Authority
GB
United Kingdom
Prior art keywords
air
compressor
icing
heated
engine
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
GB1197769A
Inventor
John Frederick Coplin
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 GB1197769A priority Critical patent/GB1210202A/en
Priority to FR7006184A priority patent/FR2031306A5/fr
Priority to DE19702010754 priority patent/DE2010754C3/en
Publication of GB1210202A publication Critical patent/GB1210202A/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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60Q—ARRANGEMENT OF SIGNALLING OR LIGHTING DEVICES, THE MOUNTING OR SUPPORTING THEREOF OR CIRCUITS THEREFOR, FOR VEHICLES IN GENERAL
    • B60Q1/00—Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor
    • B60Q1/26—Arrangement of optical signalling or lighting devices, the mounting or supporting thereof or circuits therefor the devices being primarily intended to indicate the vehicle, or parts thereof, or to give signals, to other traffic

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

1,210,202. Gas turbine engines. ROLLSROYCE Ltd. March 6, 1969, No.11977/69. Heading F1G. The invention relates to a gas turbine engine in which means are provided for supplying heated air to a member at the inlet end of the engine to effect anti-icing thereof, the air then passing into the intake of the engine. Vortex means are provided to produce vortex flow in the air stream to ensure mixing thereof with ambient air passing into the intake thereby cooling the air stream before it enters the compressor of the engine. A fairing member or bullet 21 is secured to the compressor rotor 20 by means of an annular wall member 22 and a deflector 24 is secured to the member 21 so as to define a passage therebetween through which air heated by compression in the compressor and supplied through duct 23 is passed, the heated air serving to effect anti-icing of the fairing member. A series of vortex-producing members in the form of bosses 25 are mounted at the downstream end 26 of the member 21 and cause eddying of the anti-icing air stream and so mixing of the air stream with the air flowing into the intake of the compressor so that the anti-icing air is cooled before it flows into the compressor. Some of the cooled air may pass through openings 27 and 30 into the interior of the compressor rotor so as to prevent the compressor being heated by the heated air flow. The compressor blades 17 may be made of synthetic resin material which might be damaged by the anti-icing air if it were directed on to them without first being cooled.
GB1197769A 1969-03-06 1969-03-06 Gas turbine engine Expired GB1210202A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB1197769A GB1210202A (en) 1969-03-06 1969-03-06 Gas turbine engine
FR7006184A FR2031306A5 (en) 1969-03-06 1970-02-20
DE19702010754 DE2010754C3 (en) 1969-03-06 1970-03-06 Deicing device for a gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1197769A GB1210202A (en) 1969-03-06 1969-03-06 Gas turbine engine

Publications (1)

Publication Number Publication Date
GB1210202A true GB1210202A (en) 1970-10-28

Family

ID=9996155

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1197769A Expired GB1210202A (en) 1969-03-06 1969-03-06 Gas turbine engine

Country Status (3)

Country Link
DE (1) DE2010754C3 (en)
FR (1) FR2031306A5 (en)
GB (1) GB1210202A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5230603A (en) * 1990-08-22 1993-07-27 Rolls Royce Plc Control of flow instabilities in turbomachines
FR2924409A1 (en) * 2007-12-03 2009-06-05 Airbus France Sas AIRCRAFT NACELLE COMPRISING MEANS FOR HOT AIR EXHAUST
RU2573437C1 (en) * 2014-07-25 2016-01-20 Общество с ограниченной ответственностью "Газпром трансгаз Сургут" Antiicing system of gas transfer unit with gas turbine drive
US20180087456A1 (en) * 2016-09-28 2018-03-29 Pratt & Whitney Canada Corp. Anti-icing apparatus for a nose cone of a gas turbine engine
CN113090391A (en) * 2021-05-11 2021-07-09 西北工业大学 Cap cover anti-icing heat transfer structure with air film hole and front edge impact
US20240183359A1 (en) * 2022-12-05 2024-06-06 Hamilton Sundstrand Corporation Centerbody insertion for improved cac motor cooling

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2168938B1 (en) * 1972-01-27 1974-12-13 Snecma

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5230603A (en) * 1990-08-22 1993-07-27 Rolls Royce Plc Control of flow instabilities in turbomachines
FR2924409A1 (en) * 2007-12-03 2009-06-05 Airbus France Sas AIRCRAFT NACELLE COMPRISING MEANS FOR HOT AIR EXHAUST
WO2009077688A2 (en) * 2007-12-03 2009-06-25 Airbus France Aircraft nacelle including hot air discharge means
WO2009077688A3 (en) * 2007-12-03 2009-08-20 Airbus France Aircraft nacelle including hot air discharge means
JP2011505289A (en) * 2007-12-03 2011-02-24 エアバス オペレイションズ エスエーエス Aircraft nacelle including hot air discharge means
US8448901B2 (en) 2007-12-03 2013-05-28 Airbus Operations Sas Aircraft nacelle including hot air discharge means
RU2573437C1 (en) * 2014-07-25 2016-01-20 Общество с ограниченной ответственностью "Газпром трансгаз Сургут" Antiicing system of gas transfer unit with gas turbine drive
US20180087456A1 (en) * 2016-09-28 2018-03-29 Pratt & Whitney Canada Corp. Anti-icing apparatus for a nose cone of a gas turbine engine
US10968827B2 (en) * 2016-09-28 2021-04-06 Pratt & Whitney Canada Corp. Anti-icing apparatus for a nose cone of a gas turbine engine
CN113090391A (en) * 2021-05-11 2021-07-09 西北工业大学 Cap cover anti-icing heat transfer structure with air film hole and front edge impact
US20240183359A1 (en) * 2022-12-05 2024-06-06 Hamilton Sundstrand Corporation Centerbody insertion for improved cac motor cooling

Also Published As

Publication number Publication date
DE2010754B2 (en) 1974-07-25
FR2031306A5 (en) 1970-11-13
DE2010754A1 (en) 1972-07-13
DE2010754C3 (en) 1975-03-13

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Legal Events

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