GB620270A - Improvements in or relating to turbine apparatus - Google Patents
Improvements in or relating to turbine apparatusInfo
- Publication number
- GB620270A GB620270A GB1255/47A GB125547A GB620270A GB 620270 A GB620270 A GB 620270A GB 1255/47 A GB1255/47 A GB 1255/47A GB 125547 A GB125547 A GB 125547A GB 620270 A GB620270 A GB 620270A
- Authority
- GB
- United Kingdom
- Prior art keywords
- annular
- stream
- turbine
- combustion
- chambers
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
620,270. Generating combustion products under pressure. WESTINGHOUSE ELECTRIC INTERNATIONAL CO. Jan. 14, 1947, No. 1255. Convention date, Nov. 20, 1945. [Class 51 (i)] [Also in Group XXVI] In a gas turbine plant having a straight through flow through axial flow compressor, combustion chambers, turbine and propulsion jet nozzle, the combustion chambers are annular, one within the other.' The chambers are located within a main annular airduct leading from the compressor diffuser 30 to the turbine nozzle passage 32 and are defined by four conical walls 35, 36, 37, 38. Each wall has perforations 49 of a size increasing from the up-stream end. The annular air spaces 29 are bridged at the up-stream end by a gauze screen 65. The up-stream ends of the annular flame tubes 31 are closed by radial annular plates 39 in which fuel nozzles 51 are mounted. The nozzles are fed from ring mains 53, 54 enclosed by stream-lined fairings. The up-stream end of the structure is strengthened by ribs 59. A gap is left between the combustion chamber at 42a and the shell 12 to provide a flow of air outside the part 43 of the combustion chamber. The turbine shaft is surrounded by inner and outer shells 27 between which supply pipes are located.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US620270XA | 1945-11-20 | 1945-11-20 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB620270A true GB620270A (en) | 1949-03-22 |
Family
ID=22039749
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1255/47A Expired GB620270A (en) | 1945-11-20 | 1947-01-14 | Improvements in or relating to turbine apparatus |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB620270A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2674090A (en) * | 1950-03-21 | 1954-04-06 | United Aircraft Corp | Combustion chamber for gas turbines |
US2720080A (en) * | 1952-02-01 | 1955-10-11 | Rolls Royce | Combustion equipment for gas-turbine engines with support means for supporting the flame tube from an air casing |
US2996884A (en) * | 1959-03-11 | 1961-08-22 | Rolls Royce | Combustion chamber |
US3132483A (en) * | 1960-04-25 | 1964-05-12 | Rolls Royce | Gas turbine engine combustion chamber |
DE2412120A1 (en) * | 1973-03-13 | 1974-09-19 | Snecma | ENVIRONMENTALLY FRIENDLY COMBUSTION CHAMBER FOR GAS TURBINES |
FR2356000A1 (en) * | 1976-06-21 | 1978-01-20 | Gen Electric | TURBOMACHINE COMBUSTION CHAMBER SUPPORT DEVICE |
-
1947
- 1947-01-14 GB GB1255/47A patent/GB620270A/en not_active Expired
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2674090A (en) * | 1950-03-21 | 1954-04-06 | United Aircraft Corp | Combustion chamber for gas turbines |
US2720080A (en) * | 1952-02-01 | 1955-10-11 | Rolls Royce | Combustion equipment for gas-turbine engines with support means for supporting the flame tube from an air casing |
US2996884A (en) * | 1959-03-11 | 1961-08-22 | Rolls Royce | Combustion chamber |
US3132483A (en) * | 1960-04-25 | 1964-05-12 | Rolls Royce | Gas turbine engine combustion chamber |
DE2412120A1 (en) * | 1973-03-13 | 1974-09-19 | Snecma | ENVIRONMENTALLY FRIENDLY COMBUSTION CHAMBER FOR GAS TURBINES |
FR2356000A1 (en) * | 1976-06-21 | 1978-01-20 | Gen Electric | TURBOMACHINE COMBUSTION CHAMBER SUPPORT DEVICE |
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