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GB648872A - Improvements in combustion chambers - Google Patents

Improvements in combustion chambers

Info

Publication number
GB648872A
GB648872A GB15365/48A GB1536548A GB648872A GB 648872 A GB648872 A GB 648872A GB 15365/48 A GB15365/48 A GB 15365/48A GB 1536548 A GB1536548 A GB 1536548A GB 648872 A GB648872 A GB 648872A
Authority
GB
United Kingdom
Prior art keywords
entries
air
flame tube
downstream
upstream end
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
GB15365/48A
Inventor
Matthew Lewis Nathan
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 Research and Development Ltd
Original Assignee
Power Jets Research and Development 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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB15365/48A priority Critical patent/GB648872A/en
Publication of GB648872A publication Critical patent/GB648872A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient 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)

Abstract

648,872. Generating combustion products under pressure. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. June 7, 1948, No. 15365. [Class 51 (i)] A flame tube 1 for a gas turbine engine combustion system having primary air entries 1c at the upstream end 1a and secondary and tertiary air entries 1d, 1e, 1f, 1g and 1h downstream of the primary air entries has a hollow body 6 of circular section mounted coaxially within the flame tube downstream of the primary air entries by means of a plurality of ducts 5 which lead air from the outside of the flame tube to the interior of the body. The body has a perforated baffle 7 of circular section at its upstream end through which a relatively minor quantity of air flows towards the upstream end of the flame tube and one or more openings 6a at its downstream end through which a relatively major quantity of air flows into the flame tube. The hollow body supplies the major part of the secondary air, the tertiary air being supplied through the entries 1e, 1f and 1g. The entries 1e are smaller than the entries 1f and the entries 1g which are used primarily to cool the discharge end of the flame tube are smaller than both the entries 1e, 1f. A small amount of secondary air enters through the entries 1h which are of the same diameter as the entries 1g. Specification 588,086 is referred to.
GB15365/48A 1948-06-07 1948-06-07 Improvements in combustion chambers Expired GB648872A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB15365/48A GB648872A (en) 1948-06-07 1948-06-07 Improvements in combustion chambers

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB15365/48A GB648872A (en) 1948-06-07 1948-06-07 Improvements in combustion chambers

Publications (1)

Publication Number Publication Date
GB648872A true GB648872A (en) 1951-01-17

Family

ID=10057881

Family Applications (1)

Application Number Title Priority Date Filing Date
GB15365/48A Expired GB648872A (en) 1948-06-07 1948-06-07 Improvements in combustion chambers

Country Status (1)

Country Link
GB (1) GB648872A (en)

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