GB840529A - Improvements in or relating to combustion equipment of gas turbine engines - Google Patents

Improvements in or relating to combustion equipment of gas turbine engines

Info

Publication number
GB840529A
GB840529A GB1951957A GB1951957A GB840529A GB 840529 A GB840529 A GB 840529A GB 1951957 A GB1951957 A GB 1951957A GB 1951957 A GB1951957 A GB 1951957A GB 840529 A GB840529 A GB 840529A
Authority
GB
United Kingdom
Prior art keywords
fuel
pair
annular
unions
air
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
GB1951957A
Inventor
Ralph Janes
Martin Land
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 GB1951957A priority Critical patent/GB840529A/en
Publication of GB840529A publication Critical patent/GB840529A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F02C7/22—Fuel supply systems
    • F02C7/222—Fuel flow conduits, e.g. manifolds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F23R3/60—Support structures; Attaching or mounting means

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Processes For Solid Components From Exhaust (AREA)

Abstract

840,529. Liquid fuel burners. ROLLSROYCE Ltd. June 20, 1958 [June 20, 1957], No. 19519/57. Class 75(1). [Also in Group XII] In gas turbine engine combustion equipment of the kind comprising an annular flame tube disposed within an annular air casing, a mixture of air and fuel is discharged into the flame tube through an annular burner device shown in Fig. 3. The burner comprises a pair of radiallyspaced ring members 38 which are shaped to provide an annular convergent-divergent passage 38a, 38b open at its upstream end. Fuel is supplied to the inlet end of the passage through openings 37 in a pair of fuel manifolds 35 and the mixture of fuel and air issues into the combustion space through slots in the inner and outer walls of a channel-section ring member 41 which is secured at the downstream end of the members 38. The ring members 38 are spaced apart by means of faired struts extending radially therethrough. Fuel is supplied to the manifolds 35 from the ring manifold 32 through radial pipes 30 which are connected at their inner ends to unions 34 having two pairs of limbs 34a, 34b, adjacent unions being interconnected by pairs of part-circular pipes 35. Fuel flows from one union 34 to a pair of tubes 35 on either side of it, the other pair of tubes 35 on either side of that union receiving fuel from the adjacent unions 34.
GB1951957A 1957-06-20 1957-06-20 Improvements in or relating to combustion equipment of gas turbine engines Expired GB840529A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1951957A GB840529A (en) 1957-06-20 1957-06-20 Improvements in or relating to combustion equipment of gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1951957A GB840529A (en) 1957-06-20 1957-06-20 Improvements in or relating to combustion equipment of gas turbine engines

Publications (1)

Publication Number Publication Date
GB840529A true GB840529A (en) 1960-07-06

Family

ID=10130749

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1951957A Expired GB840529A (en) 1957-06-20 1957-06-20 Improvements in or relating to combustion equipment of gas turbine engines

Country Status (1)

Country Link
GB (1) GB840529A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1202064B (en) * 1961-08-03 1965-09-30 Rolls Royce Combustion chamber for gas turbine engines
JPS5164117A (en) * 1974-10-07 1976-06-03 Rolls Royce 1971 Ltd
US4566268A (en) * 1983-05-10 1986-01-28 Bbc Aktiengesellschaft Brown, Boveri & Cie Multifuel burner
US5211005A (en) * 1992-04-16 1993-05-18 Avco Corporation High density fuel injection manifold
FR2964731A1 (en) * 2010-09-09 2012-03-16 Snecma Heat exchange device for use in turboshaft engine for cooling blade and shroud of turbine, has wall pierced with orifices to direct gas jet e.g. air jet, where each orifice includes convergent and divergent section
US9567910B2 (en) 2013-07-22 2017-02-14 Rolls-Royce Plc Fuel manifold and fuel injector arrangement for a combustion chamber
EP3553293A1 (en) * 2018-04-10 2019-10-16 Delavan, Inc. Fuel nozzle manifold system for turbomachines

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1202064B (en) * 1961-08-03 1965-09-30 Rolls Royce Combustion chamber for gas turbine engines
JPS5164117A (en) * 1974-10-07 1976-06-03 Rolls Royce 1971 Ltd
US4566268A (en) * 1983-05-10 1986-01-28 Bbc Aktiengesellschaft Brown, Boveri & Cie Multifuel burner
US5211005A (en) * 1992-04-16 1993-05-18 Avco Corporation High density fuel injection manifold
FR2964731A1 (en) * 2010-09-09 2012-03-16 Snecma Heat exchange device for use in turboshaft engine for cooling blade and shroud of turbine, has wall pierced with orifices to direct gas jet e.g. air jet, where each orifice includes convergent and divergent section
US9567910B2 (en) 2013-07-22 2017-02-14 Rolls-Royce Plc Fuel manifold and fuel injector arrangement for a combustion chamber
EP3553293A1 (en) * 2018-04-10 2019-10-16 Delavan, Inc. Fuel nozzle manifold system for turbomachines
US10605171B2 (en) 2018-04-10 2020-03-31 Delavan Inc. Fuel nozzle manifold systems for turbomachines

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