GB627644A - Improvements relating to gas-turbine-engines and combustion-equipment therefor - Google Patents

Improvements relating to gas-turbine-engines and combustion-equipment therefor

Info

Publication number
GB627644A
GB627644A GB1226547A GB1226547A GB627644A GB 627644 A GB627644 A GB 627644A GB 1226547 A GB1226547 A GB 1226547A GB 1226547 A GB1226547 A GB 1226547A GB 627644 A GB627644 A GB 627644A
Authority
GB
United Kingdom
Prior art keywords
air
combustion chamber
compressor
delivery
baffle
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
GB1226547A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB1226547A priority Critical patent/GB627644A/en
Publication of GB627644A publication Critical patent/GB627644A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • 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
    • F02C7/22—Fuel supply systems
    • F02C7/236—Fuel delivery systems comprising two or more pumps
    • F02C7/2365—Fuel delivery systems comprising two or more pumps comprising an air supply system for the atomisation of fuel

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

627,644. Generating combustion products under pressure. MORDELL, D. L. May 6, 1947, No. 12265. [Class 51 (i)] [Also in Group XXVI] In an annular combustion chamber of a gas turbine plant the air and fuel are given a swirling motion in radial planes about an axis which is a circle concentric with and lying within the combustion chamber. Air from the delivery 5 of the main compressor is conducted by pipes 13 to the eye of a centrifugal compressor 10. Fuel is injected into this air either at the inlet eye or, as shown, from pipes 14 into the pump outlet. The air-fuel mixture is deflected upstream by an annular baffle 15 and the circular crosssection 9a of the end of the chamber supports an annular eddy. Secondary air admitted at ports 16 is guided tangential to the eddy. Part of the delivery of the compressor 10 may be divided off by the inner part 15a of the baffle and directed to the space between the walls, 7, 9b. In an alternative form, the delivery of the compressor 10 may traverse the combustion chamber and be deflected upstream by a baffle on the outer wall of the combustion chamber. According to the Provisional Specification the air and gas mixture is directed across the combustion chamber by spaced segmental guides. Also in a plant with a reheating combustion chamber between the turbine stages, the primary air may be taken from the highpressure compressor delivery.
GB1226547A 1947-05-06 1947-05-06 Improvements relating to gas-turbine-engines and combustion-equipment therefor Expired GB627644A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1226547A GB627644A (en) 1947-05-06 1947-05-06 Improvements relating to gas-turbine-engines and combustion-equipment therefor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1226547A GB627644A (en) 1947-05-06 1947-05-06 Improvements relating to gas-turbine-engines and combustion-equipment therefor

Publications (1)

Publication Number Publication Date
GB627644A true GB627644A (en) 1949-08-12

Family

ID=10001376

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1226547A Expired GB627644A (en) 1947-05-06 1947-05-06 Improvements relating to gas-turbine-engines and combustion-equipment therefor

Country Status (1)

Country Link
GB (1) GB627644A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2776537A (en) * 1953-04-20 1957-01-08 Adolphe C Peterson Fuel supply and control means for turbines and turbine jets
US2825205A (en) * 1953-07-15 1958-03-04 Snecma Combustion devices especially suitable for gas turbine engines and propulsion units for aircraft
US2827759A (en) * 1950-01-18 1958-03-25 Bruno W Bruckmann Gas turbine aricraft power plant having a contraflow air-fuel combustion system
US2930193A (en) * 1955-08-29 1960-03-29 Gen Electric Cowled dome liner for combustors
US3964254A (en) * 1975-05-12 1976-06-22 St John Ward A Low velocity gas turbine with exhaust gas recycling
US3968644A (en) * 1973-08-18 1976-07-13 Motoren- Und Turbinen-Union Munchen Gmbh Fuel admitting and conditioning means on combustion chambers for gas turbine engines
US4314443A (en) * 1978-11-08 1982-02-09 Teledyne Industries, Inc. Turbine engine construction
US4561257A (en) * 1981-05-20 1985-12-31 Rolls-Royce Limited Gas turbine engine combustion apparatus
WO2007073714A1 (en) * 2005-12-24 2007-07-05 Markus Schmidt Internal combustion engine comprising a separate premixing device
CN112483249A (en) * 2020-12-15 2021-03-12 通化师范学院 High-pressure gas turbine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2827759A (en) * 1950-01-18 1958-03-25 Bruno W Bruckmann Gas turbine aricraft power plant having a contraflow air-fuel combustion system
US2776537A (en) * 1953-04-20 1957-01-08 Adolphe C Peterson Fuel supply and control means for turbines and turbine jets
US2825205A (en) * 1953-07-15 1958-03-04 Snecma Combustion devices especially suitable for gas turbine engines and propulsion units for aircraft
US2930193A (en) * 1955-08-29 1960-03-29 Gen Electric Cowled dome liner for combustors
US3968644A (en) * 1973-08-18 1976-07-13 Motoren- Und Turbinen-Union Munchen Gmbh Fuel admitting and conditioning means on combustion chambers for gas turbine engines
US3964254A (en) * 1975-05-12 1976-06-22 St John Ward A Low velocity gas turbine with exhaust gas recycling
US4314443A (en) * 1978-11-08 1982-02-09 Teledyne Industries, Inc. Turbine engine construction
US4561257A (en) * 1981-05-20 1985-12-31 Rolls-Royce Limited Gas turbine engine combustion apparatus
WO2007073714A1 (en) * 2005-12-24 2007-07-05 Markus Schmidt Internal combustion engine comprising a separate premixing device
CN112483249A (en) * 2020-12-15 2021-03-12 通化师范学院 High-pressure gas turbine

Similar Documents

Publication Publication Date Title
GB618493A (en) Improvements in or relating to a gas reaction propulsion unit
GB1478395A (en) Apparatus for supplying a mixture of fuel and air to a combustion chamber
GB610641A (en) Improvements in or relating to combustion plants with gas-cooled combustion chambers
GB791232A (en) Improvements in or relating to gas turbine power plants
GB686908A (en) Improvements in or relating to combustion apparatus for a gas turbine unit
GB629819A (en) Improvements in gas-turbine engines
GB650462A (en) Improvements in or relating to combustion apparatus
GB627644A (en) Improvements relating to gas-turbine-engines and combustion-equipment therefor
GB645258A (en) Improvements in or relating to turbines
GB616695A (en) Improvements in and relating to gas turbine power plants
GB669751A (en) Improvements relating to combustion chambers for gas turbine plants and the like
GB619251A (en) Improvements relating to combustion-equipment
GB736823A (en) Engine combustion chambers
GB654122A (en) Improvements in or relating to combustion equipment for gas-turbine engines
GB704468A (en) Improvements in or relating to combustion chambers for liquid, gaseous or pulverisedsolid fuels
GB1524217A (en) Combustion chamber for a gas turbine engine
GB899213A (en) Combustion chambers
GB699865A (en) Improvements in or relating to gas turbines
GB648699A (en) Improvements in or relating to gas-turbine engine fuel systems and liquid fuel injectors therefor
GB699267A (en) Improvements in or relating to combustion turbine units
GB620270A (en) Improvements in or relating to turbine apparatus
GB626174A (en) Improvements relating to combustion turbines
GB694484A (en) Improvements relating to combustion equipment for gas turbine engines
GB809514A (en) Improvements in or relating to combustion chambers
GB870988A (en) Improvements in or relating to a liquid fuel atomiser