SE8800465D0 - GAS TURBINE ENGINE WITH AMPLIFIER AND PREVIOUS SURFACE INJECTOR - Google Patents
GAS TURBINE ENGINE WITH AMPLIFIER AND PREVIOUS SURFACE INJECTORInfo
- Publication number
- SE8800465D0 SE8800465D0 SE8800465A SE8800465A SE8800465D0 SE 8800465 D0 SE8800465 D0 SE 8800465D0 SE 8800465 A SE8800465 A SE 8800465A SE 8800465 A SE8800465 A SE 8800465A SE 8800465 D0 SE8800465 D0 SE 8800465D0
- Authority
- SE
- Sweden
- Prior art keywords
- hollow member
- hollow
- gas
- bypass
- spraybars
- Prior art date
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
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
- Separation By Low-Temperature Treatments (AREA)
- Combustion Of Fluid Fuel (AREA)
Abstract
A plurality of circumferentially displaced hollow members (28) are positioned between an outer bypass duct and the center body of the core engine of a gas turbine. Each of the hollow members is open at the radially outward end thereof for receiving relatively cool gas from the bypass duct. Each hollow member is formed with an opening (48) in the side thereof extending substantially the full length of the hollow member near the trailing edge thereof for discharging bypass gas (49) from the bypass duct in a direction facilitating thorough mixing of the bypass gas and core gases (38). A pivoted vane (50) may be provided in this opening of each of the hollow members and these vanes are controlled to vary the airflow through the aforementioned openings. Radially extending spraybars (44) or fuel rods are provided within each hollow member adjacent opposite sides thereof so as to be cooled by the bypass air flowing through the hollow member. The spraybars are provided with a plurality of openings adjacent the sidewalls of the hollow members and corresponding openings (46) are provided in these walls so that fuel, during augmentor operation, is directed into the area between adjacent hollow members. The aft end of each hollow member is formed as a relatively wide flat surface (36) which acts as a flameholder for the fuel supplied from the spraybars and burned in the augmentor. The forward end (40) of each hollow member is curved to an angle corresponding generally to the swirl angle of core gases exhausted from the core engine so as to effect a deswirling of this gas. <IMAGE>
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US1456287A | 1987-02-13 | 1987-02-13 |
Publications (3)
Publication Number | Publication Date |
---|---|
SE8800465D0 true SE8800465D0 (en) | 1988-02-11 |
SE8800465L SE8800465L (en) | 1988-08-14 |
SE466559B SE466559B (en) | 1992-03-02 |
Family
ID=21766218
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SE8800465A SE466559B (en) | 1987-02-13 | 1988-02-11 | GAS TURBINE ENGINE WITH AMPLIFIER AND VARIABLE SURFACE INJECTOR |
Country Status (5)
Country | Link |
---|---|
JP (1) | JPS63227930A (en) |
DE (1) | DE3803992A1 (en) |
FR (1) | FR2610994B1 (en) |
GB (1) | GB2202589B (en) |
SE (1) | SE466559B (en) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE8915860U1 (en) * | 1989-02-08 | 1991-12-05 | Mtu Muenchen Gmbh | |
US5261229A (en) * | 1992-08-03 | 1993-11-16 | General Electric Company | Noise-suppressed exhaust nozzles for jet engines |
FR2712962B1 (en) * | 1993-11-24 | 1995-12-29 | Snecma | Post-combustion device comprising an improved flame catching device. |
FR2763648B1 (en) * | 1997-05-22 | 1999-07-02 | Snecma | DICHOTOMIC HEATING SYSTEM REDUCING DRY LOSSES |
US7596950B2 (en) * | 2005-09-16 | 2009-10-06 | General Electric Company | Augmentor radial fuel spray bar with counterswirling heat shield |
US7603863B2 (en) * | 2006-06-05 | 2009-10-20 | General Electric Company | Secondary fuel injection from stage one nozzle |
JP5625585B2 (en) * | 2010-07-27 | 2014-11-19 | 株式会社Ihi | Afterburner and aircraft engine |
JP6229590B2 (en) * | 2014-04-30 | 2017-11-15 | 株式会社Ihi | Afterburner and aircraft engine |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3060680A (en) * | 1957-12-30 | 1962-10-30 | Rolls Royce | By-pass gas-turbine engine and control therefor |
GB928475A (en) * | 1961-12-27 | 1963-06-12 | Rolls Royce | Improvements in or relating to by-pass gas turbine engines |
GB1029900A (en) * | 1964-11-27 | 1966-05-18 | Rolls Royce | By-pass gas turbine jet engine |
DE1923150A1 (en) * | 1968-05-08 | 1970-01-15 | Man Turbo Gmbh | Turbine jet engine |
US4335573A (en) * | 1970-09-02 | 1982-06-22 | General Electric Company | Gas turbine engine mixer |
US3698186A (en) * | 1970-12-24 | 1972-10-17 | United Aircraft Corp | Afterburner combustion apparatus |
BE795529A (en) * | 1972-02-17 | 1973-06-18 | Gen Electric | IGNITER MOUNTED ON A TURBOREACTOR THRUST INCREASING DEVICE AND AIR COOLED |
US4072008A (en) * | 1976-05-04 | 1978-02-07 | General Electric Company | Variable area bypass injector system |
JPS5641815A (en) * | 1979-09-12 | 1981-04-18 | Mitsui Toatsu Chem Inc | Purifying method for wet process phosphoric acid solution |
US4461146A (en) * | 1982-10-22 | 1984-07-24 | The United States Of America As Represented By The Secretary Of The Navy | Mixed flow swirl augmentor for turbofan engine |
-
1988
- 1988-02-04 FR FR8801282A patent/FR2610994B1/en not_active Expired - Lifetime
- 1988-02-10 DE DE19883803992 patent/DE3803992A1/en not_active Withdrawn
- 1988-02-11 GB GB8803121A patent/GB2202589B/en not_active Expired - Fee Related
- 1988-02-11 SE SE8800465A patent/SE466559B/en not_active IP Right Cessation
- 1988-02-12 JP JP2905188A patent/JPS63227930A/en active Granted
Also Published As
Publication number | Publication date |
---|---|
GB8803121D0 (en) | 1988-03-09 |
DE3803992A1 (en) | 1988-08-25 |
GB2202589A (en) | 1988-09-28 |
JPH0587652B2 (en) | 1993-12-17 |
SE8800465L (en) | 1988-08-14 |
GB2202589B (en) | 1991-10-02 |
FR2610994B1 (en) | 1993-06-11 |
FR2610994A1 (en) | 1988-08-19 |
SE466559B (en) | 1992-03-02 |
JPS63227930A (en) | 1988-09-22 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
NUG | Patent has lapsed |
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