GB960606A - Combustion apparatus for gas turbine engines - Google Patents

Combustion apparatus for gas turbine engines

Info

Publication number
GB960606A
GB960606A GB39477/60A GB3947760A GB960606A GB 960606 A GB960606 A GB 960606A GB 39477/60 A GB39477/60 A GB 39477/60A GB 3947760 A GB3947760 A GB 3947760A GB 960606 A GB960606 A GB 960606A
Authority
GB
United Kingdom
Prior art keywords
air
casing
flame tube
combustion
inlet
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
GB39477/60A
Inventor
Albert Edward Clarke
David Henry Fielding
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 GB39477/60A priority Critical patent/GB960606A/en
Priority to FR977033A priority patent/FR1397729A/en
Publication of GB960606A publication Critical patent/GB960606A/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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • 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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

960,606. Generating combustion products under pressure. JOSEPH LUCAS (INDUSTRIES) Ltd. Nov. 7, 1961 [Nov. 17, 1960], No. 39477/60. Heading F1L. A gas turbine comprising a combustion chamber having a tubular or annular flame tube mounted in spaced relationship within an air casing having an inlet at one end to which air can be supplied from a compressor to flow both within and around the flame tube, is characterized in that the downstream end of the latter is of tapering form and is provided with peripheral openings, whilst the downstream end of the air casing, which is connected to the turbine, surrounds the tapering portion of the flame tube in such relationship that air flowing around the flame tube will cause products of combustion within the flame tube to be extracted through the openings to be entrained with this air. An air casing 2 has an inlet 3 connected to a compressor and an outlet 4 connected to a turbine. A flame tube 1, mounted within an air casing 2, is provided with a burner 8 surrounded by an air swirler 9 and has apertures 6 for the flow of combustion air to the combustion zone within a frusto-conical portion 5. A corrugated ring 11 mounted between the portion 5 and a casing 10 forms an annular inlet through which cooling air enters the casing 10. Air from the annular inlet is directed around lips 13 and apertures 12 in the casing 10 which is also provided with outwardly flanged apertures 14 and has a central opening at its downstream end. A shell 15 is secured within the air casing 2 to provide a space through which cooling air can flow. A throat is defined between the casing 10 and the shell 15, whereby combustion products in the casing 10 will tend to be extracted through the openings 12, 14 to be entrained with the air flowing through the air casing 2.
GB39477/60A 1960-11-17 1960-11-17 Combustion apparatus for gas turbine engines Expired GB960606A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB39477/60A GB960606A (en) 1960-11-17 1960-11-17 Combustion apparatus for gas turbine engines
FR977033A FR1397729A (en) 1960-11-17 1964-06-04 Combustion device for gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB39477/60A GB960606A (en) 1960-11-17 1960-11-17 Combustion apparatus for gas turbine engines

Publications (1)

Publication Number Publication Date
GB960606A true GB960606A (en) 1964-06-10

Family

ID=10409762

Family Applications (1)

Application Number Title Priority Date Filing Date
GB39477/60A Expired GB960606A (en) 1960-11-17 1960-11-17 Combustion apparatus for gas turbine engines

Country Status (2)

Country Link
FR (1) FR1397729A (en)
GB (1) GB960606A (en)

Also Published As

Publication number Publication date
FR1397729A (en) 1965-04-30

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