GB594285A - Improvements relating to combustion apparatus - Google Patents

Improvements relating to combustion apparatus

Info

Publication number
GB594285A
GB594285A GB4968/44A GB496844A GB594285A GB 594285 A GB594285 A GB 594285A GB 4968/44 A GB4968/44 A GB 4968/44A GB 496844 A GB496844 A GB 496844A GB 594285 A GB594285 A GB 594285A
Authority
GB
United Kingdom
Prior art keywords
air
flame tube
stream end
baffle
shell
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
GB4968/44A
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.)
Power Jets Ltd
Original Assignee
Power Jets Ltd
Filing date
Publication date
Priority to BE461591D priority Critical patent/BE461591A/xx
Application filed by Power Jets Ltd filed Critical Power Jets Ltd
Priority to US621336A priority patent/US2475911A/en
Priority to FR918088D priority patent/FR918088A/en
Priority to CH258672D priority patent/CH258672A/en
Publication of GB594285A publication Critical patent/GB594285A/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
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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
    • 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
    • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
    • 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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • F23R3/48—Flame tube interconnectors, e.g. cross-over tubes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

594,285. Generating combustion products under pressure. POWER JETS, Ltd., and NATHAN, M. L. March 16, 1944, No. 4968. [ Class 51 (i)] [Also in Group XXVI] In a power plant for the jet propulsion of aircraft comprising preferably a double entry centrifugal compressor and a circulator assembly of combustion chambers delivering to a turbine the compressor outlets are grouped in as many pairs or pluralities as there are combustion chambers and each pair deliver air to one combustion chamber. Each combustion chamber comprises an outer shell 2, with the two air inlets 6, and a flame tube 11. Each shell terminates in a segmental opening forming part of the annular admission to the turbine. Each flame tube has a conical up-stream end 12 with perforation 13 for primary air and a burner 14. Further primary air is admitted through tangential nozzles 14a which are surrounded by a cylindrical cover 15 open at the down-stream end only. Secondary air is admitted at perforations 16 and tertiary air by perforations 24 down stream of a conical baffle 18. This baffle is supported by tubular struts 20 which are open to the exterior of the baffle and deliver cooling air to its surface. The down stream end of the flame tube is attached to the shell 2 by a perforated ring 29 and the up stream end by struts 26. In one flame tube a strut 26 is replaced by an ignition plug 25. The flame tubes and the shells are connected by coaxial tubes which also form supports for the flame tube and shells.
GB4968/44A 1944-03-16 1944-03-16 Improvements relating to combustion apparatus Expired GB594285A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
BE461591D BE461591A (en) 1944-03-16
US621336A US2475911A (en) 1944-03-16 1945-10-09 Combustion apparatus
FR918088D FR918088A (en) 1944-03-16 1945-11-28 Improvements to combustion appliances
CH258672D CH258672A (en) 1944-03-16 1945-11-30 Gas turbine engine.

Publications (1)

Publication Number Publication Date
GB594285A true GB594285A (en) 1947-11-07

Family

ID=1628169

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4968/44A Expired GB594285A (en) 1944-03-16 1944-03-16 Improvements relating to combustion apparatus

Country Status (1)

Country Link
GB (1) GB594285A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2975465A1 (en) * 2011-05-19 2012-11-23 Snecma WALL FOR TURBOMACHINE COMBUSTION CHAMBER COMPRISING AN OPTIMIZED AIR INLET ORIFICE ARRANGEMENT
EP2246627A3 (en) * 2009-04-23 2014-07-30 General Electric Company Thimble fan for a combustion system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2246627A3 (en) * 2009-04-23 2014-07-30 General Electric Company Thimble fan for a combustion system
FR2975465A1 (en) * 2011-05-19 2012-11-23 Snecma WALL FOR TURBOMACHINE COMBUSTION CHAMBER COMPRISING AN OPTIMIZED AIR INLET ORIFICE ARRANGEMENT

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