GB599974A - Installation for propulsion by reaction, notably for aircraft - Google Patents
Installation for propulsion by reaction, notably for aircraftInfo
- Publication number
- GB599974A GB599974A GB24869/45A GB2486945A GB599974A GB 599974 A GB599974 A GB 599974A GB 24869/45 A GB24869/45 A GB 24869/45A GB 2486945 A GB2486945 A GB 2486945A GB 599974 A GB599974 A GB 599974A
- Authority
- GB
- United Kingdom
- Prior art keywords
- combustion chamber
- propulsion
- aircraft
- pressure compressor
- notably
- 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
- 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
- F02K3/12—Plants including a gas turbine driving a compressor or a ducted fan characterised by having more than one gas turbine
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
Abstract
599,974. Generating combustion products under pressure. SOC. INDUSTRIELLE GENERALE DE MECANIQUE APPLIQUEE (S.I.G.M.A.). Sept. 25, 1945, Nos. 24869 and 24870. Convention dates, Dec. 30, 1944, and Feb. 26, 1945. [Class 51 (i)] [Also in Group XXVI] In a gas turbine plant for the jet-propulsion of aircraft, a combustion chamber between a low-pressure compressor 1 and the turbine 8 which drives it is brought into action when a valve 62 in the lead to the high-pressure compressor is closed. Air is taken from the early part of the combustion chamber 10a by a pipe 65 to a fan which delivers it to an auxiliary combustion chamber 67 where fuel is burnt and from which the gases are discharged into the main air stream.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR599974X | 1944-12-30 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB599974A true GB599974A (en) | 1948-03-25 |
Family
ID=8969932
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB24869/45A Expired GB599974A (en) | 1944-12-30 | 1945-09-25 | Installation for propulsion by reaction, notably for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB599974A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2201467A (en) * | 1987-02-24 | 1988-09-01 | Teledyne Ind | A turbocharged compound cycle ducted fan engine |
-
1945
- 1945-09-25 GB GB24869/45A patent/GB599974A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2201467A (en) * | 1987-02-24 | 1988-09-01 | Teledyne Ind | A turbocharged compound cycle ducted fan engine |
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