GB1280862A - Improvements in or relating to gas turbine engines - Google Patents

Improvements in or relating to gas turbine engines

Info

Publication number
GB1280862A
GB1280862A GB4815069A GB4815069A GB1280862A GB 1280862 A GB1280862 A GB 1280862A GB 4815069 A GB4815069 A GB 4815069A GB 4815069 A GB4815069 A GB 4815069A GB 1280862 A GB1280862 A GB 1280862A
Authority
GB
United Kingdom
Prior art keywords
heat
heat exchanger
compressor
engine
combustion equipment
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
GB4815069A
Inventor
Eric Hughes
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 GB4815069A priority Critical patent/GB1280862A/en
Publication of GB1280862A publication Critical patent/GB1280862A/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
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • 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
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F02C7/10—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Abstract

1280862 Gas turbine engines; pre-heating air supply ROLLS-ROYCE Ltd 24 Sept 1970 [1 Oct 1969] 48150/69 Heading F1G The invention relates to a gas turbine engine comprising a first heat exchanger in which air from the engine compressor is pre-heated, and a second heat exchanger in which a heat exchange fluid (such as sodium) is heated by heat exchange with the turbine exhaust gases, the heat exchange fluid passing to the first heat exchanger to heat the air from the compressor. The engine combustion equipment and the first heat exchanger are disposed around the engine compressor. The engine shown comprises an axial-flow compressor 14, combustion equipment 30 and a turbine 38 connected to drive the compressor also an external load by means (not shown). Air from the compressor discharges through annular diffuser 18 thence radially outwardly through the section 24b of the first heat exchanger 24 which is of annular form, then radially inwardly through the section 24a of the heat exchanger thence to the combustion equipment 30. Gases from the combustion equipment pass to the turbine 38 and discharge therefrom through diffuser 48, the exhaust gases then passing through second heat exchanger 50. The heat exchangers 24, 50 comprise tubes containing heat transfer medium and the two heat exchangers are inter-connected so that the transfer medium transfers heat from the turbine exhaust gases to the air passing to the combustion equipment.
GB4815069A 1969-10-01 1969-10-01 Improvements in or relating to gas turbine engines Expired GB1280862A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB4815069A GB1280862A (en) 1969-10-01 1969-10-01 Improvements in or relating to gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4815069A GB1280862A (en) 1969-10-01 1969-10-01 Improvements in or relating to gas turbine engines

Publications (1)

Publication Number Publication Date
GB1280862A true GB1280862A (en) 1972-07-05

Family

ID=10447574

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4815069A Expired GB1280862A (en) 1969-10-01 1969-10-01 Improvements in or relating to gas turbine engines

Country Status (1)

Country Link
GB (1) GB1280862A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2131095A (en) * 1982-11-24 1984-06-13 English Electric Co Ltd Gas turbine plant

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2131095A (en) * 1982-11-24 1984-06-13 English Electric Co Ltd Gas turbine plant

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Legal Events

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