GB1314970A - Annular combustion chamber for dissimilar fluids in swirling flow relationship - Google Patents
Annular combustion chamber for dissimilar fluids in swirling flow relationshipInfo
- Publication number
- GB1314970A GB1314970A GB3455271A GB3455271A GB1314970A GB 1314970 A GB1314970 A GB 1314970A GB 3455271 A GB3455271 A GB 3455271A GB 3455271 A GB3455271 A GB 3455271A GB 1314970 A GB1314970 A GB 1314970A
- Authority
- GB
- United Kingdom
- Prior art keywords
- annular
- walls
- passages
- fluids
- fuel
- 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
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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/38—Introducing air inside the jet
- F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02G—HOT GAS OR COMBUSTION-PRODUCT POSITIVE-DISPLACEMENT ENGINE PLANTS; USE OF WASTE HEAT OF COMBUSTION ENGINES; NOT OTHERWISE PROVIDED FOR
- F02G2243/00—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes
- F02G2243/30—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes having their pistons and displacers each in separate cylinders
- F02G2243/50—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes having their pistons and displacers each in separate cylinders having resonance tubes
- F02G2243/52—Stirling type engines having closed regenerative thermodynamic cycles with flow controlled by volume changes having their pistons and displacers each in separate cylinders having resonance tubes acoustic
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
Abstract
1314970 Combustion apparatus for gas turbine engines &c UNITED AIRCRAFT CORP 23 July 1971 [26 Oct 1970] 34552/71 Heading F1L An annular combustion chamber comprises an inner wall and an outer wall which define annular passages therebetween leading to a combustion zone, at least two dissimilar fluids being directed in swirling relation through the annular passages, the first of the fluids having a density #1 and a tangential velocity vtl and the second of the fluids having a density p2 and a tangential velocity vt2 means being provided to establish the product parameter #vt<2> of one of the fluids to be different from the corresponding product parameter of the other fluid so as to influence intermixing therebetween. Many embodiments of the invention are described. In Fig. 47 for example the annular combustion chamber is defined between inner and outer air casing walls 113, 54 and a series of annular walls 134, 138a, 140a, 138b and 140b is disposed at the inlet end'to define together with the casing walls 54, 113 dilution air passages 122, 130, 132, a pilot combustion passage 124a, a fuel and air mixing passage 126a a fuel and air mixing passage 124b and a fuel and air mixing passage 126b. Rings of swirl waves 116, 118a, 120a, 118b, 120b and 128 are disposed at the upstream ends of the passages. Flame holder devices in the form of perforated frusto-conical walls 161a, 161b are provided in the passages 124a, 124b. Fuel injection devices 422, 424, 426 are provided. Trigger devices 164, 166, 169 are provided at the downstream ends of the walls 138a, 138b, 140b to facilitate burning. The annular flame tube is defined by the walls 134, 140b together with downstream extensions which are radially spaced apart by swirl waves 172, 174, 176, 168, 170. The air inlet from the compressor is indicated at 114 and the outlet to the turbine at 46. The axis of the chamber is shown at 16, the pilot combustion zone at 160a, the main combustion zone at 60 and the dilution zone at 62.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US8408670A | 1970-10-26 | 1970-10-26 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1314970A true GB1314970A (en) | 1973-04-26 |
Family
ID=22182799
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB3455271A Expired GB1314970A (en) | 1970-10-26 | 1971-07-23 | Annular combustion chamber for dissimilar fluids in swirling flow relationship |
Country Status (7)
Country | Link |
---|---|
US (1) | US3788065A (en) |
AU (1) | AU451788B2 (en) |
CA (1) | CA954313A (en) |
DE (1) | DE2153085A1 (en) |
FR (1) | FR2112339B1 (en) |
GB (1) | GB1314970A (en) |
SE (1) | SE389893B (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2269449A (en) * | 1992-08-05 | 1994-02-09 | Snecma | Combustion chamber with fuel injectors of different types |
Families Citing this family (47)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2221621B1 (en) * | 1973-03-13 | 1976-09-10 | Snecma | |
US3872664A (en) * | 1973-10-15 | 1975-03-25 | United Aircraft Corp | Swirl combustor with vortex burning and mixing |
US3999378A (en) * | 1974-01-02 | 1976-12-28 | General Electric Company | Bypass augmentation burner arrangement for a gas turbine engine |
US3974646A (en) * | 1974-06-11 | 1976-08-17 | United Technologies Corporation | Turbofan engine with augmented combustion chamber using vorbix principle |
US3937008A (en) * | 1974-12-18 | 1976-02-10 | United Technologies Corporation | Low emission combustion chamber |
US4058977A (en) * | 1974-12-18 | 1977-11-22 | United Technologies Corporation | Low emission combustion chamber |
US3973395A (en) * | 1974-12-18 | 1976-08-10 | United Technologies Corporation | Low emission combustion chamber |
US3973390A (en) * | 1974-12-18 | 1976-08-10 | United Technologies Corporation | Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones |
US4045956A (en) * | 1974-12-18 | 1977-09-06 | United Technologies Corporation | Low emission combustion chamber |
US3931707A (en) * | 1975-01-08 | 1976-01-13 | General Electric Company | Augmentor flameholding apparatus |
US3993449A (en) * | 1975-04-07 | 1976-11-23 | City Of North Olmsted | Apparatus for pollution abatement |
FR2312653A2 (en) * | 1975-05-30 | 1976-12-24 | Snecma | Secondary combustion chamber for gas turbine - has additional fuel supplied through holes in radial vanes for improved combustion |
US4012904A (en) * | 1975-07-17 | 1977-03-22 | Chrysler Corporation | Gas turbine burner |
US4204402A (en) * | 1976-05-07 | 1980-05-27 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Reduction of nitric oxide emissions from a combustor |
US4149373A (en) * | 1977-08-29 | 1979-04-17 | United Technologies Corporation | Combustion chamber stress reducing means |
US4194358A (en) * | 1977-12-15 | 1980-03-25 | General Electric Company | Double annular combustor configuration |
US4226083A (en) * | 1978-01-19 | 1980-10-07 | United Technologies Corporation | Method and apparatus for reducing nitrous oxide emissions from combustors |
US4389848A (en) * | 1981-01-12 | 1983-06-28 | United Technologies Corporation | Burner construction for gas turbines |
US4928479A (en) * | 1987-12-28 | 1990-05-29 | Sundstrand Corporation | Annular combustor with tangential cooling air injection |
US5076053A (en) * | 1989-08-10 | 1991-12-31 | United Technologies Corporation | Mechanism for accelerating heat release of combusting flows |
US5207064A (en) * | 1990-11-21 | 1993-05-04 | General Electric Company | Staged, mixed combustor assembly having low emissions |
US5197278A (en) * | 1990-12-17 | 1993-03-30 | General Electric Company | Double dome combustor and method of operation |
US5406799A (en) * | 1992-06-12 | 1995-04-18 | United Technologies Corporation | Combustion chamber |
US5335501A (en) * | 1992-11-16 | 1994-08-09 | General Electric Company | Flow spreading diffuser |
US5470224A (en) * | 1993-07-16 | 1995-11-28 | Radian Corporation | Apparatus and method for reducing NOx , CO and hydrocarbon emissions when burning gaseous fuels |
US5407347A (en) * | 1993-07-16 | 1995-04-18 | Radian Corporation | Apparatus and method for reducing NOx, CO and hydrocarbon emissions when burning gaseous fuels |
JPH08270950A (en) * | 1995-02-01 | 1996-10-18 | Mitsubishi Heavy Ind Ltd | Gas turbine combustor |
US6058710A (en) * | 1995-03-08 | 2000-05-09 | Bmw Rolls-Royce Gmbh | Axially staged annular combustion chamber of a gas turbine |
US6125627A (en) * | 1998-08-11 | 2000-10-03 | Allison Advanced Development Company | Method and apparatus for spraying fuel within a gas turbine engine |
DE59812944D1 (en) * | 1998-09-16 | 2005-08-25 | Alstom Technology Ltd Baden | Method for preventing flow instabilities in a burner |
CA2501862C (en) * | 2002-10-10 | 2010-09-21 | Combustion Science & Engineering, Inc. | System for vaporization of liquid fuels for combustion and method of use |
BRPI0518830B1 (en) * | 2004-12-08 | 2019-06-04 | Lpp Combustion,Llc | METHOD AND APPARATUS FOR CONDITIONING FUELS OF LIQUID HYDROCARBON |
US8529646B2 (en) * | 2006-05-01 | 2013-09-10 | Lpp Combustion Llc | Integrated system and method for production and vaporization of liquid hydrocarbon fuels for combustion |
US7827797B2 (en) * | 2006-09-05 | 2010-11-09 | General Electric Company | Injection assembly for a combustor |
EP2006606A1 (en) * | 2007-06-21 | 2008-12-24 | Siemens Aktiengesellschaft | Swirling-free stabilising of the flame of a premix burner |
US7775791B2 (en) * | 2008-02-25 | 2010-08-17 | General Electric Company | Method and apparatus for staged combustion of air and fuel |
FR2941742B1 (en) * | 2009-02-05 | 2011-08-19 | Snecma | DIFFUSER-RECTIFIER ASSEMBLY FOR A TURBOMACHINE |
RU2534189C2 (en) * | 2010-02-16 | 2014-11-27 | Дженерал Электрик Компани | Gas turbine combustion chamber (versions) and method of its operation |
ES2488404T3 (en) * | 2011-03-07 | 2014-08-27 | Eads Construcciones Aeronáuticas, S.A. | Flow evacuation system for an aircraft engine |
EP2500640A1 (en) * | 2011-03-16 | 2012-09-19 | L'AIR LIQUIDE, Société Anonyme pour l'Etude et l'Exploitation des Procédés Georges Claude | Low NOx combustion process and burner therefor |
US20140190178A1 (en) * | 2011-08-11 | 2014-07-10 | Beckett Gas, Inc. | Combustor |
US8943832B2 (en) * | 2011-10-26 | 2015-02-03 | General Electric Company | Fuel nozzle assembly for use in turbine engines and methods of assembling same |
EP2644997A1 (en) * | 2012-03-26 | 2013-10-02 | Alstom Technology Ltd | Mixing arrangement for mixing fuel with a stream of oxygen containing gas |
US9677766B2 (en) * | 2012-11-28 | 2017-06-13 | General Electric Company | Fuel nozzle for use in a turbine engine and method of assembly |
EP2837771A1 (en) * | 2013-08-16 | 2015-02-18 | Siemens Aktiengesellschaft | Design of an axial diffuser taking built-in components into account |
US10876407B2 (en) * | 2017-02-16 | 2020-12-29 | General Electric Company | Thermal structure for outer diameter mounted turbine blades |
US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2477683A (en) * | 1942-09-30 | 1949-08-02 | Turbo Engineering Corp | Compressed air and combustion gas flow in turbine power plant |
DE847091C (en) * | 1944-05-13 | 1952-08-21 | Daimler Benz Ag | Hot air jet engine |
US2720750A (en) * | 1947-11-04 | 1955-10-18 | Helmut R Schelp | Revolving fuel injection system for jet engines and gas turbines |
US2627720A (en) * | 1948-10-08 | 1953-02-10 | Packard Motor Car Co | Circumferentially arranged combustion chamber with arcuate walls defining an air flow path between chambers |
US2773350A (en) * | 1950-01-31 | 1956-12-11 | Hillard E Barrett | Combustion chamber assembly for ram jet fuel burner |
BE502037A (en) * | 1950-03-21 | |||
US3002351A (en) * | 1951-01-26 | 1961-10-03 | David H Sloan | Ramjet device |
US3088281A (en) * | 1956-04-03 | 1963-05-07 | Bristol Siddeley Engines Ltd | Combustion chambers for use with swirling combustion supporting medium |
US2945349A (en) * | 1957-11-12 | 1960-07-19 | Lear Inc | Miniature gas turbine |
US3034297A (en) * | 1958-12-15 | 1962-05-15 | Bristol Siddeley Engines Ltd | Combustion chambers |
FR1094871A (en) * | 1959-01-22 | 1955-05-25 | Thomson Houston Comp Francaise | Improvements to injected fuel combustion devices |
US3078672A (en) * | 1959-03-28 | 1963-02-26 | Maschf Augsburg Nuernberg Ag | Process and apparatus for operating a continuous or intermittent combustion engine |
US3373562A (en) * | 1966-03-17 | 1968-03-19 | Wingaersheek Turbine Co Inc | Combustion chamber for gas turbines and the like having improved flame holder |
GB1170255A (en) * | 1966-07-01 | 1969-11-12 | Rolls Royce | Combustion Apparatus. |
US3393516A (en) * | 1966-12-05 | 1968-07-23 | United Aircraft Corp | Curved exhaust deflector |
-
1970
- 1970-10-26 US US00084086A patent/US3788065A/en not_active Expired - Lifetime
-
1971
- 1971-07-23 GB GB3455271A patent/GB1314970A/en not_active Expired
- 1971-07-29 AU AU31779/71A patent/AU451788B2/en not_active Expired
- 1971-07-30 CA CA119,605A patent/CA954313A/en not_active Expired
- 1971-08-31 FR FR7132183A patent/FR2112339B1/fr not_active Expired
- 1971-09-08 SE SE7401957-1A patent/SE389893B/en unknown
- 1971-10-25 DE DE19712153085 patent/DE2153085A1/en not_active Ceased
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2269449A (en) * | 1992-08-05 | 1994-02-09 | Snecma | Combustion chamber with fuel injectors of different types |
GB2269449B (en) * | 1992-08-05 | 1995-06-28 | Snecma | Combustion chamber with fuel injectors of different types |
Also Published As
Publication number | Publication date |
---|---|
DE2153085A1 (en) | 1972-04-27 |
AU451788B2 (en) | 1974-08-15 |
SE7401957L (en) | 1974-02-14 |
SE389893B (en) | 1976-11-22 |
FR2112339B1 (en) | 1976-03-26 |
US3788065A (en) | 1974-01-29 |
FR2112339A1 (en) | 1972-06-16 |
CA954313A (en) | 1974-09-10 |
AU3177971A (en) | 1973-02-01 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PCNP | Patent ceased through non-payment of renewal fee |