GB2018362A – Gas turbine engine cooling
– Google Patents
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
1978-04-06
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.)
1978-04-06
Filing date
1979-03-28
Publication date
1979-10-17
1979-03-28
Application filed by Rolls Royce PLC
filed
Critical
Rolls Royce PLC
1979-03-28
Priority to GB7910994A
priority
Critical
patent/GB2018362B/en
1979-10-17
Publication of GB2018362A
publication
Critical
patent/GB2018362A/en
1982-04-21
Application granted
granted
Critical
1982-04-21
Publication of GB2018362B
publication
Critical
patent/GB2018362B/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
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.
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 (10)
* 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 MàNchen 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
1979
1979-03-28
GB
GB7910994A
patent/GB2018362B/en
not_active
Expired
Cited By (19)
* 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 MàNchen 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
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
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
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
Also Published As
Publication number
Publication date
GB2018362B
(en)
1982-04-21
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Legal Events
Date
Code
Title
Description
1994-11-23
PCNP
Patent ceased through non-payment of renewal fee
Effective date:
19940328
