GB739093A - Combustion chambers for jet-propulsion engines, gas turbines or other prime movers - Google Patents

Combustion chambers for jet-propulsion engines, gas turbines or other prime movers

Info

Publication number
GB739093A
GB739093A GB612653A GB612653A GB739093A GB 739093 A GB739093 A GB 739093A GB 612653 A GB612653 A GB 612653A GB 612653 A GB612653 A GB 612653A GB 739093 A GB739093 A GB 739093A
Authority
GB
United Kingdom
Prior art keywords
air
flame tube
inlets
annular
disposed
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
GB612653A
Inventor
John Stanley Clarke
Squire Ronald Jackson
Geoffrey John Hudson
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.)
ZF International UK Ltd
Original Assignee
Lucas Industries Ltd
Joseph Lucas Industries Ltd
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 Lucas Industries Ltd, Joseph Lucas Industries Ltd filed Critical Lucas Industries Ltd
Priority to GB612653A priority Critical patent/GB739093A/en
Priority to US480955A priority patent/US2833115A/en
Publication of GB739093A publication Critical patent/GB739093A/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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

739,093. Generating combustion products under pressure. LUCAS (INDUSTRIES), Ltd., J. March 4, 1954 [March 5, 1953], No. 6126/53. Class 51 (1). In combustion equipment for a gas turbine or a jet propulsion engine of the kind comprising an annular flame tube disposed in an annular air casing, a hollow annular nose-piece i is disposed at the inlet of the flame tube to guide air into the inner and outer annular air jackets. Disposed within the nose-piece i is a number of equi-spaced tubular air scoops o which guide air passing to either one of the air jacket spaces c, d into a number of inlets g into the flame tube. The tubular air scoops shown guide air passing into the inner air jacket space d into the inlets g. The air inlets g are disposed centrally of conicalshaped wall segments e which together form a complete annular wall at the inlet end of the flame tube. Each of the tubular air scoops may be provided with a number of guide vanes p. Additional air may be supplied to the flame tube through inlets such as q.
GB612653A 1953-03-05 1953-03-05 Combustion chambers for jet-propulsion engines, gas turbines or other prime movers Expired GB739093A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB612653A GB739093A (en) 1953-03-05 1953-03-05 Combustion chambers for jet-propulsion engines, gas turbines or other prime movers
US480955A US2833115A (en) 1953-03-05 1955-01-10 Air-jacketed annular combustion chambers for jet-propulsion engines, gas turbines or the like

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB612653A GB739093A (en) 1953-03-05 1953-03-05 Combustion chambers for jet-propulsion engines, gas turbines or other prime movers

Publications (1)

Publication Number Publication Date
GB739093A true GB739093A (en) 1955-10-26

Family

ID=9808893

Family Applications (1)

Application Number Title Priority Date Filing Date
GB612653A Expired GB739093A (en) 1953-03-05 1953-03-05 Combustion chambers for jet-propulsion engines, gas turbines or other prime movers

Country Status (1)

Country Link
GB (1) GB739093A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3035481A1 (en) * 2015-04-23 2016-10-28 Snecma TURBOMACHINE COMBUSTION CHAMBER COMPRISING A SPECIFICALLY SHAPED AIR FLOW GUIDING DEVICE

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3035481A1 (en) * 2015-04-23 2016-10-28 Snecma TURBOMACHINE COMBUSTION CHAMBER COMPRISING A SPECIFICALLY SHAPED AIR FLOW GUIDING DEVICE
WO2017013318A1 (en) * 2015-04-23 2017-01-26 Safran Aircraft Engines Turbomachine combustion chamber comprising an airflow guide device of specific shape
US10443850B2 (en) 2015-04-23 2019-10-15 Safran Aircraft Engines Turbomachine combustion chamber comprising an airflow guide device of specific shape

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