GB1252194A - - Google Patents

Info

Publication number
GB1252194A
GB1252194A GB1252194DA GB1252194A GB 1252194 A GB1252194 A GB 1252194A GB 1252194D A GB1252194D A GB 1252194DA GB 1252194 A GB1252194 A GB 1252194A
Authority
GB
United Kingdom
Prior art keywords
oct
holes
respect
enters
shroud
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
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 US76795368A priority Critical
Application filed filed Critical
Publication of GB1252194A publication Critical patent/GB1252194A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/10Air inlet arrangements for primary air
    • F23R3/12Air inlet arrangements for primary air inducing a vortex
    • F23R3/14Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • Y02T50/675

Abstract

1,252,194. Spray burners. UNITED AIRCRAFT CORP. 8 Oct., 1969 [16 Oct., 1968], No. 49335/69. Heading F4T. [Also in Division F1] In order to reduce smoke formation in the combustion apparatus of a gas turbine engine 1 to 3 % of the total air-flow through the apparatus enters the flame tube through holes 46 in a shroud 22 surrounding fuel nozzle 30 and 6 to 10% enters past swirl vanes 24. Holes 46 are inclined with respect to nozzle axis 48 and also with respect to the radial direction, the latter inclination being between 18 and 35 degrees.
GB1252194D 1968-10-16 1969-10-08 Expired GB1252194A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US76795368A true 1968-10-16 1968-10-16

Publications (1)

Publication Number Publication Date
GB1252194A true GB1252194A (en) 1971-11-03

Family

ID=25081076

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1252194D Expired GB1252194A (en) 1968-10-16 1969-10-08

Country Status (9)

Country Link
US (1) US3498055A (en)
BE (1) BE740301A (en)
BR (1) BR6913369D0 (en)
CH (1) CH500438A (en)
DE (1) DE1951198C3 (en)
FR (1) FR2020807A1 (en)
GB (1) GB1252194A (en)
IL (1) IL33166A (en)
NL (1) NL6915585A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2919857A1 (en) * 1978-05-20 1979-11-29 Rolls Royce Combustion chamber for gas turbine engine plants

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1934700B2 (en) * 1969-07-09 1972-01-05 Mtu Muenchen Gmbh Fuel nozzle for gas turbine engine plants
US3630024A (en) * 1970-02-02 1971-12-28 Gen Electric Air swirler for gas turbine combustor
US3643430A (en) * 1970-03-04 1972-02-22 United Aircraft Corp Smoke reduction combustion chamber
USRE30160E (en) * 1970-03-04 1979-11-27 United Technologies Corporation Smoke reduction combustion chamber
US3656298A (en) * 1970-11-27 1972-04-18 Gen Motors Corp Combustion apparatus
US3741483A (en) * 1971-12-10 1973-06-26 Mitsubishi Heavy Ind Ltd Combustion air supply arrangement for gas turbines
US3916619A (en) * 1972-10-30 1975-11-04 Hitachi Ltd Burning method for gas turbine combustor and a construction thereof
JPS5342897B2 (en) * 1972-11-09 1978-11-15
GB1429677A (en) * 1973-03-20 1976-03-24 Rolls Royce Gas turbine engine combustion equipment
US3901446A (en) * 1974-05-09 1975-08-26 Us Air Force Induced vortex swirler
US4155220A (en) * 1977-01-21 1979-05-22 Westinghouse Electric Corp. Combustion apparatus for a gas turbine engine
US4151713A (en) * 1977-03-15 1979-05-01 United Technologies Corporation Burner for gas turbine engine
GB2099978A (en) * 1981-05-11 1982-12-15 Rolls Royce Gas turbine engine combustor
US5297385A (en) * 1988-05-31 1994-03-29 United Technologies Corporation Combustor
FR2673705B1 (en) * 1991-03-06 1994-12-16 Snecma
DE60110392T2 (en) 2000-02-14 2006-03-09 Potencia Medical Ag Hydraulic device for the treatment of harnine continence
DE102006041955A1 (en) * 2006-08-30 2008-03-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Method for controlling combustion in a combustion chamber and combustion chamber device
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
US9027350B2 (en) * 2009-12-30 2015-05-12 Rolls-Royce Corporation Gas turbine engine having dome panel assembly with bifurcated swirler flow
US9599343B2 (en) * 2012-11-28 2017-03-21 General Electric Company Fuel nozzle for use in a turbine engine and method of assembly
US9228747B2 (en) * 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2560207A (en) * 1948-02-04 1951-07-10 Wright Aeronautical Corp Annular combustion chamber with circumferentially spaced double air-swirl burners
US2700416A (en) * 1949-06-30 1955-01-25 Rolls Royce Fuel injection means for gas-turbine engines and combustion equipment used therewith
US2982099A (en) * 1956-10-09 1961-05-02 Rolls Royce Fuel injection arrangement in combustion equipment for gas turbine engines
US3134229A (en) * 1961-10-02 1964-05-26 Gen Electric Combustion chamber

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2919857A1 (en) * 1978-05-20 1979-11-29 Rolls Royce Combustion chamber for gas turbine engine plants

Also Published As

Publication number Publication date
DE1951198A1 (en) 1970-05-14
DE1951198B2 (en) 1973-05-17
BR6913369D0 (en) 1973-06-26
CH500438A (en) 1970-12-15
NL6915585A (en) 1970-04-20
FR2020807A1 (en) 1970-07-17
DE1951198C3 (en) 1973-12-06
US3498055A (en) 1970-03-03
IL33166D0 (en) 1970-03-22
IL33166A (en) 1973-08-29
BE740301A (en) 1970-03-16

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee