GB788557A - Main combustion chambers for gas turbine engines - Google Patents

Main combustion chambers for gas turbine engines

Info

Publication number
GB788557A
GB788557A GB9886/55A GB988655A GB788557A GB 788557 A GB788557 A GB 788557A GB 9886/55 A GB9886/55 A GB 9886/55A GB 988655 A GB988655 A GB 988655A GB 788557 A GB788557 A GB 788557A
Authority
GB
United Kingdom
Prior art keywords
igniter
baffle
air
baffle plate
chambers
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
GB9886/55A
Inventor
Morris Amos Stokes
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.)
Armstrong Siddeley Motors Ltd
Original Assignee
Armstrong Siddeley Motors 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 Armstrong Siddeley Motors Ltd filed Critical Armstrong Siddeley Motors Ltd
Publication of GB788557A publication Critical patent/GB788557A/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • 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
    • F02C7/26—Starting; Ignition
    • F02C7/264—Ignition
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion

Landscapes

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

Abstract

788,557. Ignitingburners. ARMSTRONG SIDDELEY MOTORS. Ltd. March 8, 1956 [April 5, 1955], No. 9886/55. Class 75(3) [Also in Group XII] The invention relates to main combustion equipment of a gas turbine engine of the kind comprising either a tubular or an annular flame tube disposed within an outer air casing, the flame tube having at its upstream end a base or baffle plate 21 which supports on its downstream side one or more J-shaped pipes 22 into the open upsteam ends of which fuel is injected with primary air. The baffle plate also supports a number of devices for admission of further combustion-supporting air. According to the invention, the baffle plate 21 also carries on its upstream side an igniter chamber 25 which is provided with an opening 26 at its upstream end for the supply of primary air, a baffle means 27, an injector 31 for supplying starting fuel into the primary air downstream of the baffle, and an igniter 34. At least one opening 35 is provided for admission of secondary air into the igniter chamber. The igniter flame issues through an outlet 36 into the flame tube. The combustion equipment shown is of the annular type comprising an annular flame tube 14, 14a ... 18, 18a disposed between inner and outer air casing walls 11, 12, the baffle plate 21 being of ring form and supporting two igniter chambers 25. The baffle 27 within the igniter chamber has a central aperture 33 and is supported by rivets 30; a cylindrical baffle 28 surrounds the baffle 27. The injector 31 discharges through the aperture 33. The devices for admission of further combustion supporting air mounted on the baffle plate 21 may each comprise a thimble-shaped member formed with a slit, and the igniter chambers 25 may be fitted in place of two of the thimble members. the igniter chambers being designed so that when not fuctioning as ignition chambers. they provide the same air flow as the thimble members they replace. In a second embodiment oxygen is supplied to the igniter chamber through a duct disposed around the fuel supply pipe thereto. Specifications 603,485 and 623,531 [both in Group XII] are referred to.
GB9886/55A 1955-04-05 1955-04-05 Main combustion chambers for gas turbine engines Expired GB788557A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB351449X 1955-04-05

Publications (1)

Publication Number Publication Date
GB788557A true GB788557A (en) 1958-01-02

Family

ID=10374347

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9886/55A Expired GB788557A (en) 1955-04-05 1955-04-05 Main combustion chambers for gas turbine engines

Country Status (4)

Country Link
BE (1) BE546730A (en)
CH (1) CH351449A (en)
FR (1) FR1144928A (en)
GB (1) GB788557A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109340822A (en) * 2018-10-08 2019-02-15 西北工业大学 Micro-engine combustion chamber built-in circular baffle spiral evaporator tube
CZ308533B6 (en) * 2016-05-19 2020-10-29 První Brněnská Strojírna Velká Bíteš, A.S. Small turbine engine with ignition system
CN114151200A (en) * 2021-10-20 2022-03-08 中国航发四川燃气涡轮研究院 Igniter
EP4019839A3 (en) * 2020-12-23 2022-10-12 Collins Engine Nozzles, Inc. Torch ignitors with gas assist start
CN117869126A (en) * 2024-03-12 2024-04-12 西安航天动力研究所 A direct current ignition structure for a rocket engine combustion chamber

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1102491B (en) * 1957-10-19 1961-03-16 Bristol Siddeley Engines Ltd Combustion device for a gas turbine engine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CZ308533B6 (en) * 2016-05-19 2020-10-29 První Brněnská Strojírna Velká Bíteš, A.S. Small turbine engine with ignition system
CN109340822A (en) * 2018-10-08 2019-02-15 西北工业大学 Micro-engine combustion chamber built-in circular baffle spiral evaporator tube
EP4019839A3 (en) * 2020-12-23 2022-10-12 Collins Engine Nozzles, Inc. Torch ignitors with gas assist start
US11708793B2 (en) 2020-12-23 2023-07-25 Collins Engine Nozzles, Inc. Torch ignitors with gas assist start
US12031482B2 (en) 2020-12-23 2024-07-09 Delavan, Inc. Torch ignitors with gas assist start
CN114151200A (en) * 2021-10-20 2022-03-08 中国航发四川燃气涡轮研究院 Igniter
CN117869126A (en) * 2024-03-12 2024-04-12 西安航天动力研究所 A direct current ignition structure for a rocket engine combustion chamber

Also Published As

Publication number Publication date
BE546730A (en)
CH351449A (en) 1961-01-15
FR1144928A (en) 1957-10-18

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