FR2008096A1 - - Google Patents
Info
- Publication number
- FR2008096A1 FR2008096A1 FR6914821A FR6914821A FR2008096A1 FR 2008096 A1 FR2008096 A1 FR 2008096A1 FR 6914821 A FR6914821 A FR 6914821A FR 6914821 A FR6914821 A FR 6914821A FR 2008096 A1 FR2008096 A1 FR 2008096A1
- Authority
- FR
- France
- 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.)
- Withdrawn
Links
Classifications
-
- 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
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
- F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
-
- 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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection 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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/22—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants movable, e.g. to an inoperative position; adjustable, e.g. self-adjusting
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AT442568 | 1968-05-08 |
Publications (1)
Publication Number | Publication Date |
---|---|
FR2008096A1 true FR2008096A1 (fr) | 1970-01-16 |
Family
ID=3563845
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR6914821A Withdrawn FR2008096A1 (fr) | 1968-05-08 | 1969-05-08 |
Country Status (4)
Country | Link |
---|---|
US (1) | US3595024A (fr) |
DE (1) | DE1923150A1 (fr) |
FR (1) | FR2008096A1 (fr) |
GB (1) | GB1245673A (fr) |
Families Citing this family (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3698186A (en) * | 1970-12-24 | 1972-10-17 | United Aircraft Corp | Afterburner combustion apparatus |
US3732059A (en) * | 1971-05-28 | 1973-05-08 | Zink Co John | Burner for gaseous fuels in reduced oxygen and/or significant velocity atmosphere |
US3747345A (en) * | 1972-07-24 | 1973-07-24 | United Aircraft Corp | Shortened afterburner construction for turbine engine |
US4398388A (en) * | 1976-12-27 | 1983-08-16 | United Technologies Corporation | High bypass ratio supplemental fuel injection |
GB1605456A (en) * | 1977-03-05 | 2008-07-16 | Rolls Royce | Improvements in or relating to reheat system for gas turbine engines |
US4285194A (en) * | 1979-04-23 | 1981-08-25 | General Electric Company | Apparatus and method for controlling fan duct flow in a gas turbine engine |
US4305248A (en) * | 1979-10-05 | 1981-12-15 | The United States Of America As Represented By The Secretary Of The Air Force | Hot spike mixer |
US5001898A (en) * | 1986-08-29 | 1991-03-26 | United Technologies Corporation | Fuel distributor/flameholder for a duct burner |
FR2610994B1 (fr) * | 1987-02-13 | 1993-06-11 | Gen Electric | Moteur a turbine a gaz avec dispositif de postcombustion et injecteur de dilution a section variable |
US4817378A (en) * | 1987-02-13 | 1989-04-04 | General Electric Company | Gas turbine engine with augmentor and variable area bypass injector |
US5076062A (en) * | 1987-11-05 | 1991-12-31 | General Electric Company | Gas-cooled flameholder assembly |
US5020318A (en) * | 1987-11-05 | 1991-06-04 | General Electric Company | Aircraft engine frame construction |
FR2626044A1 (fr) * | 1988-01-14 | 1989-07-21 | Snecma | Melangeur de flux a section variable avec stabilisateur de rechauffe integre pour turboreacteur double flux |
US4901527A (en) * | 1988-02-18 | 1990-02-20 | General Electric Company | Low turbulence flame holder mount |
FR2637018A1 (fr) * | 1988-09-28 | 1990-03-30 | Snecma | Dispositif d'injection de gaz pour propulseur combine turbo-stato-fusee |
DE8915860U1 (fr) * | 1989-02-08 | 1991-12-05 | Mtu Muenchen Gmbh | |
US5070690A (en) * | 1989-04-26 | 1991-12-10 | General Electric Company | Means and method for reducing differential pressure loading in an augmented gas turbine engine |
US5117628A (en) * | 1990-01-25 | 1992-06-02 | General Electric Company | Mixed flow augmentor pre-mixer |
US5261229A (en) * | 1992-08-03 | 1993-11-16 | General Electric Company | Noise-suppressed exhaust nozzles for jet engines |
FR2699227B1 (fr) * | 1992-12-16 | 1995-01-13 | Snecma | Ensemble monobloc de post-combustion d'une turbine à gaz. |
FR2712962B1 (fr) * | 1993-11-24 | 1995-12-29 | Snecma | Dispositif de postcombustion comprenant un dispositif accroche-flammes perfectionné. |
FR2856744B1 (fr) * | 2003-06-25 | 2007-05-25 | Snecma Moteurs | Canaux de ventilation sur tole de confluence d'une chambre de post-combustion |
US7712315B2 (en) * | 2006-04-20 | 2010-05-11 | United Technologies Corporation | Augmentor variable vane flame stabilization |
US20100146980A1 (en) * | 2007-05-22 | 2010-06-17 | Volvo Aero Corporation | masking arrangement for a gas turbine engine |
US8713909B2 (en) * | 2009-03-04 | 2014-05-06 | United Technologies Corporation | Elimination of unfavorable outflow margin |
EP2381071A1 (fr) * | 2010-04-21 | 2011-10-26 | Siemens Aktiengesellschaft | Diffuseur de gaz d'échappement d'une turbine à gaz |
US20130174534A1 (en) * | 2012-01-05 | 2013-07-11 | General Electric Company | System and device for controlling fluid flow through a gas turbine exhaust |
US8534071B1 (en) * | 2012-04-06 | 2013-09-17 | United Technologies Corporation | Engine hot section vane with tapered flame holder surface |
GB2615335A (en) * | 2022-02-04 | 2023-08-09 | Rolls Royce Plc | A reheat assembly |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3118276A (en) * | 1964-01-21 | Gas turbine engines | ||
GB852829A (en) * | 1957-04-03 | 1960-11-02 | Rolls Royce | Improvements in or relating to gas-turbine jet propulsion engines |
US2934895A (en) * | 1958-09-15 | 1960-05-03 | Curtiss Wright Corp | Dual cycle engine distributor construction |
NL110872C (fr) * | 1959-03-13 | |||
GB1043524A (en) * | 1962-06-05 | 1966-09-21 | Bristol Siddeley Engines Ltd | Improvements in jet propulsion engines |
GB1064675A (en) * | 1962-11-26 | 1967-04-05 | Bristol Siddeley Engines Ltd | Improvements in nozzles for discharge of compressible fluid |
US3330117A (en) * | 1964-11-27 | 1967-07-11 | Rolls Royce | By-pass gas turbine jet engine |
-
1969
- 1969-05-07 DE DE19691923150 patent/DE1923150A1/de active Pending
- 1969-05-08 US US822968A patent/US3595024A/en not_active Expired - Lifetime
- 1969-05-08 GB GB23611/69A patent/GB1245673A/en not_active Expired
- 1969-05-08 FR FR6914821A patent/FR2008096A1/fr not_active Withdrawn
Also Published As
Publication number | Publication date |
---|---|
DE1923150A1 (de) | 1970-01-15 |
GB1245673A (en) | 1971-09-08 |
US3595024A (en) | 1971-07-27 |
Similar Documents
Legal Events
Date | Code | Title | Description |
---|---|---|---|
CD | Change of name or company name | ||
ST | Notification of lapse |