GB1105630A - Combustion apparatus for gas turbine engines - Google Patents

Combustion apparatus for gas turbine engines

Info

Publication number
GB1105630A
GB1105630A GB3557865A GB3557865A GB1105630A GB 1105630 A GB1105630 A GB 1105630A GB 3557865 A GB3557865 A GB 3557865A GB 3557865 A GB3557865 A GB 3557865A GB 1105630 A GB1105630 A GB 1105630A
Authority
GB
United Kingdom
Prior art keywords
openings
combustion
zone
gas turbine
outer zone
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
GB3557865A
Inventor
Keith Lambert Barker
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 GB3557865A priority Critical patent/GB1105630A/en
Publication of GB1105630A publication Critical patent/GB1105630A/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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

1,105,630. Gas turbine combustion chambers. JOSEPH LUCAS (INDUSTRIES) Ltd. Aug. 23, 1966 [Aug. 19, 1965], No.35578/65. Heading F1L. Combustion apparatus for a gas turbine engine comprises an annular flame tube divided by an annular wall 24 into a combustion zone 16 and an outer zone 17. Openings 18 leading to the combustion zone 16 alternate with openings 19 leading to the outer zone 17. Primary air, together with fuel supplied by burner nozzles 21, enters the combustion zone 16 through the openings 18. A deflector plate 25 causes the flow of combustion gases to tend to form two toroidal flow patterns. The combustion gases pass from the combustion zone 16 to the outer zone 17 through openings 23 aligned lengthwise of the flame tube with the openings 19. Dilution air enters the outer zone 17 through the openings 19, each of which is provided with a deflector plate 20.
GB3557865A 1965-08-19 1965-08-19 Combustion apparatus for gas turbine engines Expired GB1105630A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3557865A GB1105630A (en) 1965-08-19 1965-08-19 Combustion apparatus for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3557865A GB1105630A (en) 1965-08-19 1965-08-19 Combustion apparatus for gas turbine engines

Publications (1)

Publication Number Publication Date
GB1105630A true GB1105630A (en) 1968-03-06

Family

ID=10379291

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3557865A Expired GB1105630A (en) 1965-08-19 1965-08-19 Combustion apparatus for gas turbine engines

Country Status (1)

Country Link
GB (1) GB1105630A (en)

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