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GB715909A - 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
GB715909A
GB715909A GB2793/52A GB279352A GB715909A GB 715909 A GB715909 A GB 715909A GB 2793/52 A GB2793/52 A GB 2793/52A GB 279352 A GB279352 A GB 279352A GB 715909 A GB715909 A GB 715909A
Authority
GB
United Kingdom
Prior art keywords
struts
flame tube
strut
wall
downstream
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
GB2793/52A
Inventor
George Oulianoff
Jeffrey Evans
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 GB2793/52A priority Critical patent/GB715909A/en
Priority to US332812A priority patent/US2720080A/en
Priority to FR1073579D priority patent/FR1073579A/en
Priority to CH309297D priority patent/CH309297A/en
Publication of GB715909A publication Critical patent/GB715909A/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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

715,909. Generating combustion products under pressure. ROLLS-ROYCE, Ltd. Jan. 2t, 1953 [Feb. 1, 1952], No. 2793/32. Class 51 (1) In an annular air-jacketed type of combustion chamber of a gas turbine engine, struts 10c connect the inner and outer walls 10b, 10a of the air casing and the downstream ends of the struts and the inlet end of the annular flame tube overlap in the axial direction, the overlap being accommodated by means of notch-like features formed in the two parts. Pins 31 extend through aligned bores 29, 30 in the struts and an adjacent part of the flame tube to locate 'the latter with respect to the struts. The struts are hollow and the downstream edge of a strut 10c is recessed at 21, 22, 23, the surfaces 21, 22 being parallel to the adjacent walls of the upstream portion 15 of the flame tube and the surface 23 being radially disposed. The upstream portion 15 of the flame tube is wedge-shaped and comprises walls 18a, 18b, 18c and 19, 25. The part 19 is cut away at 24 to accommodate the downstream end of a strut 10e, the cut-away being closed by blanking pieces 25. A socket member 28 is secured to the wall 18c and the bore 28a therein is aligned with bores 29, 30 formed in the downstream end of the strut 10c, the pair 31 passing therethrough and being secured in position by means of a circlip 33. Axially-directed pins 26 mounted on the wall 25 engage spigots 27 formed in the strut wall 23. Two fuel injectors 34 are located between each pair of struts 10c and are located at the centre of frusto-conical parts 20 mounted in the trough 18a, 18b, 18c of the flame tube. The fuel injectors may be surrounded by swirl vanes 35 and shroud members 36. Specification 715,910 is referred to.
GB2793/52A 1952-02-01 1952-02-01 Improvements in or relating to combustion equipment of gas-turbine engines Expired GB715909A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB2793/52A GB715909A (en) 1952-02-01 1952-02-01 Improvements in or relating to combustion equipment of gas-turbine engines
US332812A US2720080A (en) 1952-02-01 1953-01-23 Combustion equipment for gas-turbine engines with support means for supporting the flame tube from an air casing
FR1073579D FR1073579A (en) 1952-02-01 1953-01-27 Improvements to the combustion equipment of gas turbine engines
CH309297D CH309297A (en) 1952-02-01 1953-01-30 Combustion device in gas turbine plants.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2793/52A GB715909A (en) 1952-02-01 1952-02-01 Improvements in or relating to combustion equipment of gas-turbine engines

Publications (1)

Publication Number Publication Date
GB715909A true GB715909A (en) 1954-09-22

Family

ID=9746016

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2793/52A Expired GB715909A (en) 1952-02-01 1952-02-01 Improvements in or relating to combustion equipment of gas-turbine engines

Country Status (4)

Country Link
US (1) US2720080A (en)
CH (1) CH309297A (en)
FR (1) FR1073579A (en)
GB (1) GB715909A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2134243A (en) * 1983-01-27 1984-08-08 Rolls Royce Combustion equipment for a gas turbine engine
GB2135440A (en) * 1983-02-19 1984-08-30 Rolls Royce Mounting combustion chambers
GB2263733A (en) * 1992-01-28 1993-08-04 Snecma Turbomachine with removable combustion chamber.
US20160223196A1 (en) * 2015-02-02 2016-08-04 The Government Of The United States Of America, As Represented By The Secretary Of The Navy Crude Oil Spray Combustor

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB736823A (en) * 1953-01-19 1955-09-14 Lucas Industries Ltd Engine combustion chambers
US2852914A (en) * 1955-12-30 1958-09-23 United Aircraft Corp Combustion chamber support means
DE1096682B (en) * 1959-08-26 1961-01-05 Entwicklungsbau Pirna Veb Annular combustion chamber for gas turbines
US3049882A (en) * 1960-05-16 1962-08-21 Gen Electric Combustor construction with means for prevention of hot streaks
GB1021588A (en) * 1963-12-04 1966-03-02 Rolls Royce Combustion equipment for a gas turbine engine
US3512359A (en) * 1968-05-24 1970-05-19 Gen Electric Dummy swirl cup combustion chamber
US3670497A (en) * 1970-09-02 1972-06-20 United Aircraft Corp Combustion chamber support
US3978664A (en) * 1974-12-20 1976-09-07 United Technologies Corporation Gas turbine engine diffuser
US4098074A (en) * 1976-06-01 1978-07-04 United Technologies Corporation Combustor diffuser for turbine type power plant and construction thereof
GB2097112B (en) * 1981-04-16 1984-12-12 Rolls Royce Fuel burners and combustion equipment for use in gas turbine engines
US4628694A (en) * 1983-12-19 1986-12-16 General Electric Company Fabricated liner article and method
US4785623A (en) * 1987-12-09 1988-11-22 United Technologies Corporation Combustor seal and support
EP0363834B1 (en) * 1988-10-12 1994-04-13 Ruhrgas Aktiengesellschaft Burner, particularly a high-speed burner
FR2706534B1 (en) * 1993-06-10 1995-07-21 Snecma Multiflux diffuser-separator with integrated rectifier for turbojet.
US8800290B2 (en) * 2007-12-18 2014-08-12 United Technologies Corporation Combustor
US8448444B2 (en) * 2011-02-18 2013-05-28 General Electric Company Method and apparatus for mounting transition piece in combustor
US10260742B2 (en) * 2012-06-22 2019-04-16 Ferndale Investments Pty Ltd Heating torch
US9273868B2 (en) * 2013-08-06 2016-03-01 General Electric Company System for supporting bundled tube segments within a combustor
GB201408690D0 (en) * 2014-05-16 2014-07-02 Rolls Royce Plc A combustion chamber arrangement
GB201505502D0 (en) * 2015-03-31 2015-05-13 Rolls Royce Plc Combustion equipment

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB620270A (en) * 1945-11-20 1949-03-22 Westinghouse Electric Int Co Improvements in or relating to turbine apparatus
US2552851A (en) * 1949-10-25 1951-05-15 Westinghouse Electric Corp Combustion chamber with retrorse baffles for preheating the fuelair mixture

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2134243A (en) * 1983-01-27 1984-08-08 Rolls Royce Combustion equipment for a gas turbine engine
GB2135440A (en) * 1983-02-19 1984-08-30 Rolls Royce Mounting combustion chambers
US4525996A (en) * 1983-02-19 1985-07-02 Rolls-Royce Limited Mounting combustion chambers
GB2263733A (en) * 1992-01-28 1993-08-04 Snecma Turbomachine with removable combustion chamber.
GB2263733B (en) * 1992-01-28 1995-01-18 Snecma Turbomachine with removable combustion chamber
US20160223196A1 (en) * 2015-02-02 2016-08-04 The Government Of The United States Of America, As Represented By The Secretary Of The Navy Crude Oil Spray Combustor

Also Published As

Publication number Publication date
FR1073579A (en) 1954-09-27
US2720080A (en) 1955-10-11
CH309297A (en) 1955-08-31

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