GB657865A - Improvements in or relating to fuel combustion apparatus - Google Patents
Improvements in or relating to fuel combustion apparatusInfo
- Publication number
- GB657865A GB657865A GB7331/49A GB733149A GB657865A GB 657865 A GB657865 A GB 657865A GB 7331/49 A GB7331/49 A GB 7331/49A GB 733149 A GB733149 A GB 733149A GB 657865 A GB657865 A GB 657865A
- Authority
- GB
- United Kingdom
- Prior art keywords
- spider
- arms
- nozzles
- combustion chamber
- 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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
657,865. Gas turbine plant. WESTING- HOUSE ELECTRIC INTERNATIONAL CO. March 17, 1949, No. 7331. Convention date, April 27, 1948. [Class 110(iii)] [Also in Groups XI and XII] In a gas turbine plant, fuel is injected into an annular combustion chamber 20 by nozzles 31 carried on the arms of a spider 40 rotating with the turbine shaft. Fuel is delivered to an annular cavity 42 in the hub of the spider and passes through radial ducts 43 to the nozzles. The annular gap 29 in the combustion chamber will is substantially closed by a rim 50 which joins the arms of the spider. The parts of the spider arms within the combustion chamber are formed as axial flow blades; the blade portions 46, 48 producing a downstream flow of the gases and the portion 47, an upstream flow. The nozzles 31 are directed towards the shaft axis. In a modification, the nzzles are carried by a plain ring supported from the hub by arms that cross the air duct 13.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US23589A US2568921A (en) | 1948-04-27 | 1948-04-27 | Combustion chamber with rotating fuel nozzles |
Publications (1)
Publication Number | Publication Date |
---|---|
GB657865A true GB657865A (en) | 1951-09-26 |
Family
ID=21816056
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB7331/49A Expired GB657865A (en) | 1948-04-27 | 1949-03-17 | Improvements in or relating to fuel combustion apparatus |
Country Status (2)
Country | Link |
---|---|
US (1) | US2568921A (en) |
GB (1) | GB657865A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2691096A (en) * | 1951-09-27 | 1954-10-05 | Rca Corp | Radio frequency tank circuit |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2922278A (en) * | 1948-11-30 | 1960-01-26 | Szydlowski Joseph | Coaxial combustion products generator and turbine |
US2659196A (en) * | 1949-08-09 | 1953-11-17 | United Aircraft Corp | Centrifugal fuel supply means for jet engine afterburners |
US3036428A (en) * | 1950-12-16 | 1962-05-29 | Curtiss Wright Corp | Self-feeding rocket motor |
US2693083A (en) * | 1951-03-26 | 1954-11-02 | Roy W Abbott | Combination flame-holder and fuel nozzle |
US2784551A (en) * | 1951-06-01 | 1957-03-12 | Orin M Raphael | Vortical flow gas turbine with centrifugal fuel injection |
US3029603A (en) * | 1951-10-26 | 1962-04-17 | Howard E Brown | Air bled fuel injector system |
US2925714A (en) * | 1954-10-11 | 1960-02-23 | Thompson Ramo Wooldridge Inc | Diffuser-regenerator gas turbine engine |
US3524319A (en) * | 1955-05-03 | 1970-08-18 | Bolkow Gmbh | Rocket engine with cooling walls of combustion chamber with oxygensupplying liquid |
US3126705A (en) * | 1956-03-26 | 1964-03-31 | Combustion system | |
US2865174A (en) * | 1956-05-16 | 1958-12-23 | United Aircraft Corp | Screech reduction in combustion chambers |
US2952123A (en) * | 1956-05-25 | 1960-09-13 | Lockheed Aircraft Corp | Directional controls for propulsive jets |
US2974489A (en) * | 1957-07-03 | 1961-03-14 | Paul C Holden | Internal combustion engine apparatus |
US7896620B1 (en) | 2007-02-22 | 2011-03-01 | Florida Turbine Technologies, Inc. | Integral gas turbine compressor and rotary fuel injector |
US8006500B1 (en) * | 2008-01-29 | 2011-08-30 | Florida Turbine Technologies, Inc. | Swirl combustor with counter swirl fuel slinger |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2400714A (en) * | 1942-06-11 | 1946-05-21 | Rowledge Arthur John | Jet propulsion power unit |
US2416389A (en) * | 1942-06-17 | 1947-02-25 | Armstrong Siddeley Motors Ltd | Torque balancing of jet propulsion turbine plant |
-
1948
- 1948-04-27 US US23589A patent/US2568921A/en not_active Expired - Lifetime
-
1949
- 1949-03-17 GB GB7331/49A patent/GB657865A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2691096A (en) * | 1951-09-27 | 1954-10-05 | Rca Corp | Radio frequency tank circuit |
Also Published As
Publication number | Publication date |
---|---|
US2568921A (en) | 1951-09-25 |
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