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GB940195A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
GB940195A
GB940195A GB9891/62A GB989162A GB940195A GB 940195 A GB940195 A GB 940195A GB 9891/62 A GB9891/62 A GB 9891/62A GB 989162 A GB989162 A GB 989162A GB 940195 A GB940195 A GB 940195A
Authority
GB
United Kingdom
Prior art keywords
flame tube
burner
wall
openings
gas turbine
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
GB9891/62A
Inventor
Betram Harry Urmston
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 GB9891/62A priority Critical patent/GB940195A/en
Publication of GB940195A publication Critical patent/GB940195A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Gas Burners (AREA)

Abstract

940,195. Gas turbines etc; combustion chambers. ROLLS-ROYCE Ltd. March 14, 1962. No. 9891/62. Heading F1L. A gas turbine engine has an engine casing in which the upstream end of a single annular flame tube is supported from the casing solely by a plurality of radially extending burner devices through which fuel may be supplied to the flame tube. An annular flame tube 17 having a frusto-conical portion 21 and an internal wall 22 is supported from the engine casing 11 at its upstream end solely by burners 32 passing freely through openings 33 in the portion 21, openings 34 in the wall 25, and holes in brackets 35 secured to the wall 22. Each burner 32 has main and pilot fuel paths leading to a discharge orifice 40 whose axis is at right angles to the longitudinal axis of the burner. The nozzle guide vanes 23 have apertures 24 through which air passes to passages 30, 31 for cabin pressurisation as described in Specification 932,000,
GB9891/62A 1962-03-14 1962-03-14 Gas turbine engine Expired GB940195A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB9891/62A GB940195A (en) 1962-03-14 1962-03-14 Gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9891/62A GB940195A (en) 1962-03-14 1962-03-14 Gas turbine engine

Publications (1)

Publication Number Publication Date
GB940195A true GB940195A (en) 1963-10-23

Family

ID=9880709

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9891/62A Expired GB940195A (en) 1962-03-14 1962-03-14 Gas turbine engine

Country Status (1)

Country Link
GB (1) GB940195A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5134855A (en) * 1989-12-15 1992-08-04 Rolls-Royce Plc Air flow diffuser with path splitter to control fluid flow
WO1997004218A1 (en) * 1995-07-19 1997-02-06 Siemens Aktiengesellschaft Cast housing for the exhaust gas connection piece of a turbo machine, in particular a steam turbine
US6030176A (en) * 1995-07-19 2000-02-29 Siemens Aktiengesellschaft Structural member for an exhaust-gas connection of a turbomachine, in particular a steam turbine, and set of at least two structural members

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5134855A (en) * 1989-12-15 1992-08-04 Rolls-Royce Plc Air flow diffuser with path splitter to control fluid flow
WO1997004218A1 (en) * 1995-07-19 1997-02-06 Siemens Aktiengesellschaft Cast housing for the exhaust gas connection piece of a turbo machine, in particular a steam turbine
US6030176A (en) * 1995-07-19 2000-02-29 Siemens Aktiengesellschaft Structural member for an exhaust-gas connection of a turbomachine, in particular a steam turbine, and set of at least two structural members

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