GB2018362A - Gas turbine engine cooling - Google Patents

Gas turbine engine cooling

Info

Publication number
GB2018362A
GB2018362A GB7910994A GB7910994A GB2018362A GB 2018362 A GB2018362 A GB 2018362A GB 7910994 A GB7910994 A GB 7910994A GB 7910994 A GB7910994 A GB 7910994A GB 2018362 A GB2018362 A GB 2018362A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
turbine engine
engine cooling
cooling air
duct means
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.)
Granted
Application number
GB7910994A
Other versions
GB2018362B (en
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 GB7910994A priority Critical patent/GB2018362B/en
Publication of GB2018362A publication Critical patent/GB2018362A/en
Application granted granted Critical
Publication of GB2018362B publication Critical patent/GB2018362B/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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

The engine combustion system has an initial diffusing section (21), and duct means (28) to convey cooling air from at least part way down the diffusing section, to the turbine. At least one aperture (39) in the duct means (28) allows part of the cooling air to flow forwardly along the outer surface of the engine shaft (15) to cool it. <IMAGE>
GB7910994A 1978-04-06 1979-03-28 Gas turbine engine cooling Expired GB2018362B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7910994A GB2018362B (en) 1978-04-06 1979-03-28 Gas turbine engine cooling

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1342278 1978-04-06
GB7910994A GB2018362B (en) 1978-04-06 1979-03-28 Gas turbine engine cooling

Publications (2)

Publication Number Publication Date
GB2018362A true GB2018362A (en) 1979-10-17
GB2018362B GB2018362B (en) 1982-04-21

Family

ID=26249766

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7910994A Expired GB2018362B (en) 1978-04-06 1979-03-28 Gas turbine engine cooling

Country Status (1)

Country Link
GB (1) GB2018362B (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0235642A2 (en) * 1986-02-28 1987-09-09 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Arrangement for the aeration of compressor rotor parts of gas turbine power units
FR2653170A1 (en) * 1989-10-16 1991-04-19 Gen Electric HIGH PRESSURE AIR SUPPLY DEVICE WITH TURBINE MACHINE TURBINE ROTOR BLADES AND METHOD FOR REDUCING PRESSURE LOSS IN THE INTERIOR CHANNEL OF THE COMBUSTION CHAMBER OF A TURBOMACHINE.
US5142859A (en) * 1991-02-22 1992-09-01 Solar Turbines, Incorporated Turbine cooling system
FR2695161A1 (en) * 1992-08-26 1994-03-04 Snecma Cooling system for a turbomachine compressor and clearance control.
US5586860A (en) * 1993-11-03 1996-12-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbo aero engine provided with a device for heating turbine disks on revving up
WO1997023715A2 (en) * 1995-12-21 1997-07-03 Siemens Aktiengesellschaft Process for operating a gas turbine and gas turbine operating in this way
US6234746B1 (en) * 1999-08-04 2001-05-22 General Electric Co. Apparatus and methods for cooling rotary components in a turbine
EP1111189A3 (en) * 1999-12-22 2004-01-07 Rolls-Royce Deutschland GmbH Cooling air path for the rotor of a gas turbine engine
WO2014133659A1 (en) * 2013-03-01 2014-09-04 Rolls-Royce North American Technologies, Inc. High pressure compressor thermal management and method of assembly and cooling
EP2843194A3 (en) * 2013-09-03 2015-03-18 MTU Aero Engines GmbH Gas engine with a cooling device of the compressor
CN115870702A (en) * 2022-12-07 2023-03-31 中国航发动力股份有限公司 Machining method for ensuring width of flow channel of inner sleeve of casing
CN117287267A (en) * 2023-11-24 2023-12-26 成都中科翼能科技有限公司 Turbine disc cavity structure of gas turbine
CN115870702B (en) * 2022-12-07 2024-04-30 中国航发动力股份有限公司 Machining method for guaranteeing width of inner sleeve runner of casing

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0235642A2 (en) * 1986-02-28 1987-09-09 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Arrangement for the aeration of compressor rotor parts of gas turbine power units
EP0235642A3 (en) * 1986-02-28 1989-07-05 Mtu Muenchen Gmbh Arrangement for the aeration of compressor rotor parts of gas turbine power units
FR2653170A1 (en) * 1989-10-16 1991-04-19 Gen Electric HIGH PRESSURE AIR SUPPLY DEVICE WITH TURBINE MACHINE TURBINE ROTOR BLADES AND METHOD FOR REDUCING PRESSURE LOSS IN THE INTERIOR CHANNEL OF THE COMBUSTION CHAMBER OF A TURBOMACHINE.
GB2237068A (en) * 1989-10-16 1991-04-24 Gen Electric Cooling air flow in a turbo-machine
DE4018316A1 (en) * 1989-10-16 1991-04-25 Gen Electric DEVICE FOR SUPPLYING TURBINE BLADES WITH HIGH PRESSURE COOLING AIR AND METHOD FOR REDUCING PRESSURE LOSS
US5187931A (en) * 1989-10-16 1993-02-23 General Electric Company Combustor inner passage with forward bleed openings
GB2237068B (en) * 1989-10-16 1994-05-25 Gen Electric Cooling rotor blades
US5142859A (en) * 1991-02-22 1992-09-01 Solar Turbines, Incorporated Turbine cooling system
FR2695161A1 (en) * 1992-08-26 1994-03-04 Snecma Cooling system for a turbomachine compressor and clearance control.
US5297386A (en) * 1992-08-26 1994-03-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Cooling system for a gas turbine engine compressor
US5586860A (en) * 1993-11-03 1996-12-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbo aero engine provided with a device for heating turbine disks on revving up
WO1997023715A2 (en) * 1995-12-21 1997-07-03 Siemens Aktiengesellschaft Process for operating a gas turbine and gas turbine operating in this way
WO1997023715A3 (en) * 1995-12-21 1997-09-04 Siemens Ag Process for operating a gas turbine and gas turbine operating in this way
US6234746B1 (en) * 1999-08-04 2001-05-22 General Electric Co. Apparatus and methods for cooling rotary components in a turbine
EP1111189A3 (en) * 1999-12-22 2004-01-07 Rolls-Royce Deutschland GmbH Cooling air path for the rotor of a gas turbine engine
WO2014133659A1 (en) * 2013-03-01 2014-09-04 Rolls-Royce North American Technologies, Inc. High pressure compressor thermal management and method of assembly and cooling
US9816963B2 (en) 2013-03-01 2017-11-14 Rolls-Royce North American Technologies, Inc. High pressure compressor thermal management
EP2843194A3 (en) * 2013-09-03 2015-03-18 MTU Aero Engines GmbH Gas engine with a cooling device of the compressor
US9822797B2 (en) 2013-09-03 2017-11-21 MTU Aero Engines AG Turbomachine
CN115870702A (en) * 2022-12-07 2023-03-31 中国航发动力股份有限公司 Machining method for ensuring width of flow channel of inner sleeve of casing
CN115870702B (en) * 2022-12-07 2024-04-30 中国航发动力股份有限公司 Machining method for guaranteeing width of inner sleeve runner of casing
CN117287267A (en) * 2023-11-24 2023-12-26 成都中科翼能科技有限公司 Turbine disc cavity structure of gas turbine
CN117287267B (en) * 2023-11-24 2024-01-23 成都中科翼能科技有限公司 Turbine disc cavity structure of gas turbine

Also Published As

Publication number Publication date
GB2018362B (en) 1982-04-21

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Legal Events

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

Effective date: 19940328