GB1274370A - Improvements relating to fuel nozzles - Google Patents

Improvements relating to fuel nozzles

Info

Publication number
GB1274370A
GB1274370A GB33227/70A GB3322770A GB1274370A GB 1274370 A GB1274370 A GB 1274370A GB 33227/70 A GB33227/70 A GB 33227/70A GB 3322770 A GB3322770 A GB 3322770A GB 1274370 A GB1274370 A GB 1274370A
Authority
GB
United Kingdom
Prior art keywords
fuel
air
ports
chamber
holes
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
GB33227/70A
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.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of GB1274370A publication Critical patent/GB1274370A/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
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Abstract

1,274,370. Spray nozzle for turbines. MOTO. RENUND TURBINEN-UNION MUNCHEN G.m.b.H. 8 July, 1970 [9 July, 1969], No. 33227/70. Heading, F4T. A fuel nozzle 4, comprises cylindrical housing 10 and piston-type insert 11, for delivering a fuel/air mixture to a gas turbine engine and has a plurality of fuel delivery ports and a plurality of air intake ports such that when the nozzle 4 is mounted in a gas turbine engine upstream of an upstream flame tube wall 3, fuel jets emitted from the delivery ports entrain compressor air to cause it to be injected through the intake ports and preliminarily mixed with the jets before passing through transfer ports (17) to swirl chamber 18. Air flows in the directions indicated by arrows F, G, H, K, L, M, O to supply air for combustion and for cooling flame tube 2. Fuel, under pressure, is supplied through line 12 via metering orifices (13) (Figs. 5 and 6, not shown) in insert 11 into annular compartment 15, entraining air via. holes 16, the air/fuel mixture being subsequently forced through ports (17) (Figs. 5. and 6, not shown), circumferentially displaced and inclined with respect to orifices (13), and into swirl chamber 18 where the air and fuel are. thoroughly mixed and to which additional air is supplied' through tangential holes (19). A spray cone 21 may protrude from chamber 18 intoorifice. 22 to effect uniform fuel atomization and distribution, and a central fuel hole or holes 25 may supply additional fuel to chamber 18.
GB33227/70A 1969-07-09 1970-07-08 Improvements relating to fuel nozzles Expired GB1274370A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19691934700 DE1934700B2 (en) 1969-07-09 1969-07-09 FUEL NOZZLE FOR GAS TURBINE ENGINES

Publications (1)

Publication Number Publication Date
GB1274370A true GB1274370A (en) 1972-05-17

Family

ID=5739249

Family Applications (1)

Application Number Title Priority Date Filing Date
GB33227/70A Expired GB1274370A (en) 1969-07-09 1970-07-08 Improvements relating to fuel nozzles

Country Status (4)

Country Link
US (1) US3657885A (en)
DE (1) DE1934700B2 (en)
FR (1) FR2030978A5 (en)
GB (1) GB1274370A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2117274A (en) * 1982-03-26 1983-10-12 Northern Eng Ind Liquid fuel atomiser

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4600377A (en) * 1985-05-29 1986-07-15 Cedarapids, Inc. Refractoriless liquid fuel burner
GB2198518B (en) * 1986-12-10 1990-08-01 Rolls Royce Plc Combustion apparatus for a gas turbine engine
US4773596A (en) * 1987-04-06 1988-09-27 United Technologies Corporation Airblast fuel injector
SE459364B (en) * 1987-11-13 1989-06-26 Odd Olsson FOERBRAENNINGSANORDNING
US5144804A (en) * 1989-07-07 1992-09-08 Fuel Systems Textron Inc. Small airblast fuel nozzle with high efficiency inner air swirler
US5086979A (en) * 1989-07-07 1992-02-11 Fuel Systems Textron Inc. Small airblast fuel nozzle with high efficiency inner air swirler
US5167116A (en) * 1989-07-07 1992-12-01 Fuel Systems Textron Inc. Small airblast fuel nozzle with high efficiency inner air swirler
US5657631A (en) * 1995-03-13 1997-08-19 B.B.A. Research & Development, Inc. Injector for turbine engines
GB0230070D0 (en) * 2002-12-23 2003-01-29 Bowman Power Systems Ltd A combustion device
US7320440B2 (en) * 2005-02-07 2008-01-22 Pratt & Whitney Canada Corp. Low cost pressure atomizer
EP2239501B1 (en) * 2009-04-06 2012-01-04 Siemens Aktiengesellschaft Swirler, combustion chamber, and gas turbine with improved swirl
US9181812B1 (en) * 2009-05-05 2015-11-10 Majed Toqan Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2771744A (en) * 1952-05-07 1956-11-27 Rolls Royee Ltd Fuel injection means of combustion equipment for gas turbine engines
US2968925A (en) * 1959-11-25 1961-01-24 William E Blevans Fuel nozzle head for anti-coking
US3134229A (en) * 1961-10-02 1964-05-26 Gen Electric Combustion chamber
US3530667A (en) * 1967-11-02 1970-09-29 Rolls Royce Fuel injector for gas turbine engines
US3498055A (en) * 1968-10-16 1970-03-03 United Aircraft Corp Smoke reduction combustion chamber
US3570242A (en) * 1970-04-20 1971-03-16 United Aircraft Corp Fuel premixing for smokeless jet engine main burner

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2117274A (en) * 1982-03-26 1983-10-12 Northern Eng Ind Liquid fuel atomiser

Also Published As

Publication number Publication date
US3657885A (en) 1972-04-25
DE1934700A1 (en) 1971-01-28
FR2030978A5 (en) 1970-11-13
DE1934700B2 (en) 1972-01-05

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
746 Register noted 'licences of right' (sect. 46/1977)
PCNP Patent ceased through non-payment of renewal fee