GB839009A - 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
GB839009A
GB839009A GB35671/56A GB3567156A GB839009A GB 839009 A GB839009 A GB 839009A GB 35671/56 A GB35671/56 A GB 35671/56A GB 3567156 A GB3567156 A GB 3567156A GB 839009 A GB839009 A GB 839009A
Authority
GB
United Kingdom
Prior art keywords
wall
walls
flame tube
air
secured
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
GB35671/56A
Inventor
Frederick Reginald Murray
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
Priority to DENDAT1066385D priority Critical patent/DE1066385B/en
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB35671/56A priority patent/GB839009A/en
Priority to US697068A priority patent/US3019605A/en
Publication of GB839009A publication Critical patent/GB839009A/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
    • F23R3/42—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
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

839,009. Generating combustion products under pressure. ROLLS-ROYCE Ltd. Nov. 15, 1957 [Nov. 21, 1956], No. 35671/56. Class 51 (1). In combustion equipment of gas-turbine engines of the kind comprising an air casing 10 and within the easing a flame tube 11 wherein combustion occurs, the flame tube walls being spaced from the air casing to provide a passage for flow of air, and having in them circumferentially-spaced apertures 12 through which air flows into the flame tube, flow dividing walls 15 are provided in the air space 13 between the air casing and flame tube in the region of the apertures, each dividing wall extending within the air space radially of the flame tube wall and axially of the combustion equipment across an aperture to divide the air flow to the aperture. An annular radially-extending wall may be provided encircling the flame tube and joining the downstream ends of the flowdividing walls. The annular wall may lie in a plane at right angles to the flame tube axis or it may be of zig-zag form when viewed radially. The combustion equipment shown in Fig. 8 comprises an annular flame tube formed by inner and outer annular walls 22, 23 disposed within an annular air casing formed by inner and outer annular walls 20, 21 and flowdividing walls 34 are associated with the air inlet apertures 32 provided in the outer wall 23 of the flame tube, and flow-dividing walls 134 are associated with the air inlet apertures 32 in the inner wall 22 of the flame tube. The walls 34 are formed with flanges 34a, 34b, the flanges 34a being secured to the air casing wall 21, and the flanges 34b being secured to a frusto-conical annular wall 35 which is secured by its flange 35a to the outer air casing wall 21. The flow-dividing walls 134 are secured by their flanges 134a, 134c to the inner wall 22 of the flame tube at the upstream and downstream sides of the air inlet apertures 32. A frustoconical annular wall 135 is secured by its flange 135a to the inner wall 20 of the air casing, the wall 135 being slightly spaced from the downstream ends of the flow-dividing walls 134. In another arrangement, the flow-dividing walls associated with apertures in the inner wall of the flame tube are secured to the inner air casing wall similarly to the flow-dividing walls 34. The combustion equipment shown in Figs. 9 and 10 comprises a series of tubular flame tubes 42 disposed within an annular air casing afforded by annular walls 40, 41, the flame tube discharge portions 45 each having a radial flange 45a to which are secured baffle plates 46, the assembly of baffle plates substantially closing the space between the air easing walls 40, 41 and the flame tubes at its downstream end. Flow-dividing walls 47a, 476, 47c are associated with the row of air inlet openings 44 in the flame tube. The wall 47a is short radially and is secured to the flame tube by welding 48. The walls 47b are provided with flanges 50 which are secured either to a baffle plate 46 or to the radial flange 45a. The walls 47c have flanges 52 which are secured to the baffle plates 46.
GB35671/56A 1956-11-21 1956-11-21 Improvements in or relating to combustion equipment of gas turbine engines Expired GB839009A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DENDAT1066385D DE1066385B (en) 1956-11-21 Burning plant of gas tank aggregates
GB35671/56A GB839009A (en) 1956-11-21 1956-11-21 Improvements in or relating to combustion equipment of gas turbine engines
US697068A US3019605A (en) 1956-11-21 1957-11-18 Combustion apparatus of gas turbine engines with means controlling air flow conditions in the combustion apparatus

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB35671/56A GB839009A (en) 1956-11-21 1956-11-21 Improvements in or relating to combustion equipment of gas turbine engines

Publications (1)

Publication Number Publication Date
GB839009A true GB839009A (en) 1960-06-29

Family

ID=10380283

Family Applications (1)

Application Number Title Priority Date Filing Date
GB35671/56A Expired GB839009A (en) 1956-11-21 1956-11-21 Improvements in or relating to combustion equipment of gas turbine engines

Country Status (3)

Country Link
US (1) US3019605A (en)
DE (1) DE1066385B (en)
GB (1) GB839009A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3113431A (en) * 1959-11-20 1963-12-10 Rolls Royce Combustion equipment for a gas turbine engine
US3119234A (en) * 1960-09-13 1964-01-28 Rolls Royce Combustion chamber for a gas turbine engine

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS50133312A (en) * 1974-04-10 1975-10-22
US5177956A (en) * 1991-02-06 1993-01-12 Sundstrand Corporation Ultra high altitude starting compact combustor
GB0426214D0 (en) * 2004-11-30 2004-12-29 Rolls Royce Plc Combustor
FR2897143B1 (en) * 2006-02-08 2012-10-05 Snecma COMBUSTION CHAMBER OF A TURBOMACHINE
FR2899315B1 (en) * 2006-03-30 2012-09-28 Snecma CONFIGURING DILUTION OPENINGS IN A TURBOMACHINE COMBUSTION CHAMBER WALL
US9010121B2 (en) * 2010-12-10 2015-04-21 Rolls-Royce Plc Combustion chamber
US20120227408A1 (en) * 2011-03-10 2012-09-13 Delavan Inc. Systems and methods of pressure drop control in fluid circuits through swirling flow mitigation
WO2015100346A1 (en) * 2013-12-23 2015-07-02 United Technologies Corporation Multi-streamed dilution hole configuration for a gas turbine engine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2618928A (en) * 1944-05-19 1952-11-25 Power Jets Res & Dev Ltd Combustion apparatus with vaned fuel injector means
US2616258A (en) * 1946-01-09 1952-11-04 Bendix Aviat Corp Jet engine combustion apparatus, including pilot burner for ignition and vaporization of main fuel supply
US2513325A (en) * 1946-08-29 1950-07-04 Westinghouse Electric Corp Combustion apparatus
US2488911A (en) * 1946-11-09 1949-11-22 Surface Combustion Corp Combustion apparatus for use with turbines
BE482256A (en) * 1947-05-23
US2828609A (en) * 1950-04-03 1958-04-01 Bristol Aero Engines Ltd Combustion chambers including suddenly enlarged chamber portions
US2651912A (en) * 1950-10-31 1953-09-15 Gen Electric Combustor and cooling means therefor
US2756731A (en) * 1951-06-13 1956-07-31 Wille Rudolf Air-guiding means in the intake conduit of an internal combustion engine
US2770096A (en) * 1952-09-15 1956-11-13 Phillips Petroleum Co Continuous combustion chamber with air flow and turbulence controlled by flame frontposition

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3113431A (en) * 1959-11-20 1963-12-10 Rolls Royce Combustion equipment for a gas turbine engine
US3119234A (en) * 1960-09-13 1964-01-28 Rolls Royce Combustion chamber for a gas turbine engine

Also Published As

Publication number Publication date
US3019605A (en) 1962-02-06
DE1066385B (en) 1959-10-01

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