GB1043524A - Improvements in jet propulsion engines - Google Patents
Improvements in jet propulsion enginesInfo
- Publication number
- GB1043524A GB1043524A GB21687/62A GB2168762A GB1043524A GB 1043524 A GB1043524 A GB 1043524A GB 21687/62 A GB21687/62 A GB 21687/62A GB 2168762 A GB2168762 A GB 2168762A GB 1043524 A GB1043524 A GB 1043524A
- Authority
- GB
- United Kingdom
- Prior art keywords
- baffles
- fuel
- combustion
- disposed
- annular
- 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
- 238000002485 combustion reaction Methods 0.000 abstract 6
- 239000000446 fuel Substances 0.000 abstract 5
- 238000011144 upstream manufacturing Methods 0.000 abstract 2
- 238000007599 discharging Methods 0.000 abstract 1
- 238000002347 injection Methods 0.000 abstract 1
- 239000007924 injection Substances 0.000 abstract 1
- 238000005192 partition Methods 0.000 abstract 1
- 230000000087 stabilizing effect Effects 0.000 abstract 1
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
- F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
- F02K1/004—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector by using one or more swivable nozzles rotating about their own axis
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
- B64C29/0066—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors with horizontal jet and jet deflector
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Abstract
1,043,524. Gas turbine jet engines. BRISTOL SIDDELEY ENGINES Ltd. May 15, 1963 [June 5, 1962], No. 21687/62. Headings F1G and F1L. An aircraft jet propulsion power plant comprises an axial-flow air compressor which delivers air to an annular passage having at least one side outlet which communicates through a stub duct with a swivelling thrust nozzle, a plurality of struts or pillars being spaced around the passage and projecting across it transversely of the direction of airflow therethrough, each strut or pillar carrying a pair of perforated baffles which extend downstream of the strut or pillar and are arranged for relative swinging movement from an open V position with the strut or pillar constituting the apex of the V, to a closed position, there being means for dispersing fuel either into the V-shaped space between each pair of baffles when open, or into the air flowing through the perforations of the baffles into that space, for combustion therein. The engine shown is a gas turbine jet engine of the by-pass type in which air from the low pressure compressor 26 is divided by a partition wall 15 into two streams, the inner stream flowing through annular passage 13 to the high pressure compressor 20, thence through main combustion equipment 60, to high and low pressure turbines 61, 62 finally discharging through jet nozzles. The outer stream of air flows into an annular duct 14 in which is disposed combustion equipment, the duct 14 communicating with two outwardly and downwardly directed stub ducts 28 with which are associated angularly movable thrust nozzles 63 as set forth in Specification 1,013,116. The combustion space within the annular duct 14 is defined by flame tube walls 48, 49, the outer wall 49 being lipped at 59 in the regions of the stub ducts 28 as shown in Fig. 2. A series of struts or vanes 33 extends radially between the walls 23, 32 which together with the intermediate wall 15 define the annular ducts 13, 14, and at the downstream edges of the portions of the struts or vanes 33 which extend across the annular duct 14 are disposed co-axial tubes 38, 39 to which are secured perforated baffles 34, 35. The baffles 34, 35 may be moved to the open position shown in Fig. 4 in which they define a V-shaped combustion stabilizing space into which fuel may be injected through orifices 51 in the tubes 38, 39, or to a closed position in which they are disposed side-by-side and form a downstream continuation of the surfaces of the vane 33. The baffles are formed with perforations 36 and provided with internal deflectors 37. Further tubular members 44, 45 carrying baffles 42, 43 are disposed between the firstmentioned tubular members and baffles, the baffles of adjacent pairs abutting when in the open position. The baffles are adjustable by means of an angularly adjustable ring 65 which surrounds the casing 32, the ring being formed with cam grooves in which are received rollers carried by actuating levers secured to the baffles. The cam grooves may be shaped so that a first set of baffles moves to the open position upon a first angular movement of the ring, and a second set of baffles moves to the open position upon further angular movement of the ring. Fuel may be discharged from the tubular members 38, 39, 44, 45 into the spaces upstream of the baffles, the fuel being carried into the combustion spaces downstream of the baffles by the air flowing through the perforations in the baffles. Again, the fuel may be supplied through separate injection devices disposed upstream of the baffles.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB21687/62A GB1043524A (en) | 1962-06-05 | 1962-06-05 | Improvements in jet propulsion engines |
US281732A US3245218A (en) | 1962-06-05 | 1963-05-20 | Jet propulsion engine with variable baffles and fuel supply |
SE6048/63A SE304644B (en) | 1962-06-05 | 1963-05-31 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB21687/62A GB1043524A (en) | 1962-06-05 | 1962-06-05 | Improvements in jet propulsion engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1043524A true GB1043524A (en) | 1966-09-21 |
Family
ID=10167149
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB21687/62A Expired GB1043524A (en) | 1962-06-05 | 1962-06-05 | Improvements in jet propulsion engines |
Country Status (3)
Country | Link |
---|---|
US (1) | US3245218A (en) |
GB (1) | GB1043524A (en) |
SE (1) | SE304644B (en) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3381474A (en) * | 1966-06-10 | 1968-05-07 | Gen Electric | Compound aircraft and propulsion system |
GB1170255A (en) * | 1966-07-01 | 1969-11-12 | Rolls Royce | Combustion Apparatus. |
DE1923150A1 (en) * | 1968-05-08 | 1970-01-15 | Man Turbo Gmbh | Turbine jet engine |
US3701255A (en) * | 1970-10-26 | 1972-10-31 | United Aircraft Corp | Shortened afterburner construction for turbine engine |
US4527390A (en) * | 1977-10-25 | 1985-07-09 | General Motors Corporation | Low loss duct burner |
US4686826A (en) * | 1980-05-14 | 1987-08-18 | The United States Of America As Represented By The Secretary Of The Air Force | Mixed flow augmentor incorporating a fuel/air tube |
FR2687734B1 (en) * | 1992-02-26 | 1994-08-26 | Snecma | FLAME-HANGING DEVICE WITH VARIABLE GEOMETRY FOR USE IN THE POST-COMBUSTION DEVICE OF A TURBOMACHINE. |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2899799A (en) * | 1959-08-18 | Combustion control arrangement | ||
US2866313A (en) * | 1950-04-14 | 1958-12-30 | Power Jets Res & Dev Ltd | Means for cooling turbine-blades by liquid jets |
US2835108A (en) * | 1951-07-17 | 1958-05-20 | Solar Aircraft Co | Variable area flametholder for afterburner |
US2875580A (en) * | 1957-04-16 | 1959-03-03 | Westinghouse Electric Corp | Flameholding apparatus |
-
1962
- 1962-06-05 GB GB21687/62A patent/GB1043524A/en not_active Expired
-
1963
- 1963-05-20 US US281732A patent/US3245218A/en not_active Expired - Lifetime
- 1963-05-31 SE SE6048/63A patent/SE304644B/xx unknown
Also Published As
Publication number | Publication date |
---|---|
SE304644B (en) | 1968-09-30 |
US3245218A (en) | 1966-04-12 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3392529A (en) | Aircraft provided with a gas turbine vertical lift engine | |
US3299632A (en) | Combustion chamber for a gas turbine engine | |
US3100627A (en) | By-pass gas-turbine engine | |
US2934895A (en) | Dual cycle engine distributor construction | |
DE69618085T2 (en) | Method of distributing fuel in an afterburner | |
GB1389347A (en) | Gas turbine power plant | |
GB780493A (en) | Improvements relating to combustion equipment for gas-turbine engines | |
GB1182504A (en) | Jet Propulsion Nozzle | |
US3434288A (en) | By-pass gas turbine engine | |
US2734341A (en) | Reheating turbine exhaust gases | |
US3527052A (en) | Combustion system with aerodynamically variable geometry | |
GB1075958A (en) | Gas turbine engine | |
GB1451354A (en) | Aerodynamic flame holder | |
GB1110154A (en) | Aircraft jet power plant | |
GB871842A (en) | Improvements in or relating to gas turbine engines | |
US3085396A (en) | Gas turbine engine with gas starter | |
GB1043524A (en) | Improvements in jet propulsion engines | |
US3300976A (en) | Combined guide vane and combustion equipment for bypass gas turbine engines | |
US2709337A (en) | Boundary layer control for the diffuser of a gas turbine | |
GB1090147A (en) | Thrust nozzle for supersonic gas turbine jet engines of the by-pass type | |
US2782593A (en) | Multi-unit ramjet | |
GB751013A (en) | Improvements in combustion devices particularly applicable to aircraft jet propulsion units | |
US3196609A (en) | Gas turbine by-pass engine | |
GB918778A (en) | Improvements in or relating to gas-turbine engines | |
GB1204698A (en) | A turbofan engine and a method of operating said engine |