GB1112357A - Flame tube - Google Patents

Flame tube

Info

Publication number
GB1112357A
GB1112357A GB56247/66A GB5624766A GB1112357A GB 1112357 A GB1112357 A GB 1112357A GB 56247/66 A GB56247/66 A GB 56247/66A GB 5624766 A GB5624766 A GB 5624766A GB 1112357 A GB1112357 A GB 1112357A
Authority
GB
United Kingdom
Prior art keywords
flame tube
tube
air
gas turbine
swirling
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
GB56247/66A
Inventor
Jerry Ohanes Melconian
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB56247/66A priority Critical patent/GB1112357A/en
Publication of GB1112357A publication Critical patent/GB1112357A/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
    • F23R3/16—Continuous 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
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/24—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants of the fluid-screen type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/12—Fluid guiding means, e.g. vanes
    • F05B2240/121—Baffles or ribs
    • 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)

Abstract

1,112,357. Gas turbine combustion chambers. ROLLS-ROYCE Ltd. Dec.15, 1966, No.56247/66. Heading F1L. A cylindrical flame tube of a gas turbine engine has a swirl device (17), Fig.1 (not shown), for introducing into the flame tube a fuel/air mixture swirling in an anti-clockwise direction, and angularly spaced holes 21 downstream of the primary combustion zone through which baffles 22 direct secondary or dilution air swirling in the opposite, i.e. clockwise, direction to thus break up hot streaks in the burning mixture. The construction is applicable also to an annular flame tube. An outer casing (11) surrounds the flame tubes or tube to define the air space from which the secondary or dilution air is drawn.
GB56247/66A 1966-12-15 1966-12-15 Flame tube Expired GB1112357A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB56247/66A GB1112357A (en) 1966-12-15 1966-12-15 Flame tube

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB56247/66A GB1112357A (en) 1966-12-15 1966-12-15 Flame tube

Publications (1)

Publication Number Publication Date
GB1112357A true GB1112357A (en) 1968-05-01

Family

ID=10476158

Family Applications (1)

Application Number Title Priority Date Filing Date
GB56247/66A Expired GB1112357A (en) 1966-12-15 1966-12-15 Flame tube

Country Status (1)

Country Link
GB (1) GB1112357A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0803681A1 (en) * 1996-04-24 1997-10-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Optimalisation of the mixture of combustion gas in a gas turbine combustor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0803681A1 (en) * 1996-04-24 1997-10-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Optimalisation of the mixture of combustion gas in a gas turbine combustor
FR2748088A1 (en) * 1996-04-24 1997-10-31 Snecma OPTIMIZATION OF THE MIXTURE OF BURNED GASES IN AN ANNULAR COMBUSTION CHAMBER
US5934067A (en) * 1996-04-24 1999-08-10 Societe National D'etude Et De Construction De Moteurs D'aviation (Snecma) Gas turbine engine combustion chamber for optimizing the mixture of burned gases

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