GB1453611A - Cooling of gas turbine engines - Google Patents

Cooling of gas turbine engines

Info

Publication number
GB1453611A
GB1453611A GB306573A GB306573A GB1453611A GB 1453611 A GB1453611 A GB 1453611A GB 306573 A GB306573 A GB 306573A GB 306573 A GB306573 A GB 306573A GB 1453611 A GB1453611 A GB 1453611A
Authority
GB
United Kingdom
Prior art keywords
compressor
turbine
air
cooling
cooler
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
GB306573A
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 GB306573A priority Critical patent/GB1453611A/en
Publication of GB1453611A publication Critical patent/GB1453611A/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
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • 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
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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

1453611 Gas turbine plant - deriving cooling air ROLLS-ROYCE (1971) Ltd 8 Feb 1974 [20 Jan 1973] 3065/73 Heading F1G The invention relates to a gas turbine engine and to means for taking air from the compressor thereof, the air being passed through an auxiliary flow-path comprising a turbine and a compressor in series flow and being utilised for engine cooling. The compressor 10 of the main engine is shown in Fig. 1 and air is tapped therefrom and passed through a turbine 14 then through a cooler 20 then through a compressor 16 from which it is discharged for cooling parts of the main engine, for example the turbine blades thereof, the compressor 16 being driven by the turbine 14 through shaft 18. A further turbine 22 driven by exhaust gases from the main engine may be connected to assist drive of the compressor 16. In Fig. 2 the air tapped from the engine compressor 10 is first cooled in a cooler 24, a proportion of the air so cooled passing through turbine 14, cooler 20 and compressor 16 to the point of use as in Fig. 1; the remaining portion of air from the cooler 24 is passed to a second turbine 22 which assists the drive of compressor 16, the air discharging from the turbine 22 also being utilized for cooling purposes for example for cooling lower-pressure turbine blades. In Fig. 3 (not shown) air tapped from the main compressor 10 is utilized in part as in Fig. 1; the remaining part of the tapped air is passed through a cooler 24 then expanded through a turbine 22 which assists drive of the compressor 16, finally being utilized for cooling purposes.
GB306573A 1973-01-20 1973-01-20 Cooling of gas turbine engines Expired GB1453611A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB306573A GB1453611A (en) 1973-01-20 1973-01-20 Cooling of gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB306573A GB1453611A (en) 1973-01-20 1973-01-20 Cooling of gas turbine engines

Publications (1)

Publication Number Publication Date
GB1453611A true GB1453611A (en) 1976-10-27

Family

ID=9751337

Family Applications (1)

Application Number Title Priority Date Filing Date
GB306573A Expired GB1453611A (en) 1973-01-20 1973-01-20 Cooling of gas turbine engines

Country Status (1)

Country Link
GB (1) GB1453611A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1990012204A1 (en) * 1989-04-03 1990-10-18 Allied-Signal Inc. High performance turbine engine
FR2660367A1 (en) * 1990-04-02 1991-10-04 Gen Electric AUXILIARY AIR-REFRIGERATED SYSTEM EMPLOYING AIR FROM THE COMPRESSOR OF A TURBINE ENGINE AFTER DERIVATION AND AIR CONDITIONING IN THE SYSTEM.
EP0564135A2 (en) * 1992-03-23 1993-10-06 General Electric Company Gas turbine engine cooling system
EP0584958A1 (en) * 1992-08-03 1994-03-02 General Electric Company Intercooled turbine blade cooling air feed system
EP0608142A1 (en) * 1993-01-21 1994-07-27 General Electric Company Gas turbine engine cooling system
WO2002090741A1 (en) * 2001-05-10 2002-11-14 Siemens Aktiengesellschaft Method for cooling a gas turbine and gas turbine installation

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1990012204A1 (en) * 1989-04-03 1990-10-18 Allied-Signal Inc. High performance turbine engine
FR2660367A1 (en) * 1990-04-02 1991-10-04 Gen Electric AUXILIARY AIR-REFRIGERATED SYSTEM EMPLOYING AIR FROM THE COMPRESSOR OF A TURBINE ENGINE AFTER DERIVATION AND AIR CONDITIONING IN THE SYSTEM.
EP0564135A2 (en) * 1992-03-23 1993-10-06 General Electric Company Gas turbine engine cooling system
EP0564135A3 (en) * 1992-03-23 1994-03-23 Gen Electric
US5392614A (en) * 1992-03-23 1995-02-28 General Electric Company Gas turbine engine cooling system
EP0584958A1 (en) * 1992-08-03 1994-03-02 General Electric Company Intercooled turbine blade cooling air feed system
EP0608142A1 (en) * 1993-01-21 1994-07-27 General Electric Company Gas turbine engine cooling system
WO2002090741A1 (en) * 2001-05-10 2002-11-14 Siemens Aktiengesellschaft Method for cooling a gas turbine and gas turbine installation

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Legal Events

Date Code Title Description
CSNS Application of which complete specification have been accepted and published, but patent is not sealed