GB629920A - Improvements in jet propulsion plants, in particular for aircraft - Google Patents
Improvements in jet propulsion plants, in particular for aircraftInfo
- Publication number
- GB629920A GB629920A GB31703/47A GB3170347A GB629920A GB 629920 A GB629920 A GB 629920A GB 31703/47 A GB31703/47 A GB 31703/47A GB 3170347 A GB3170347 A GB 3170347A GB 629920 A GB629920 A GB 629920A
- Authority
- GB
- United Kingdom
- Prior art keywords
- compressor
- air
- working
- series
- turbine
- 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 3
- 239000012530 fluid Substances 0.000 abstract 2
- 238000010079 rubber tapping Methods 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B71/00—Free-piston engines; Engines without rotary main shaft
- F02B71/04—Adaptations of such engines for special use; Combinations of such engines with apparatus driven thereby
- F02B71/06—Free-piston combustion gas generators per se
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/02—Plural gas-turbine plants having a common power output
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B75/00—Other engines
- F02B75/02—Engines characterised by their cycles, e.g. six-stroke
- F02B2075/022—Engines characterised by their cycles, e.g. six-stroke having less than six strokes per cycle
- F02B2075/025—Engines characterised by their cycles, e.g. six-stroke having less than six strokes per cycle two
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
629,920. Jet-propulsion gas turbine plant. SOC. INDUSTRIELLE GENERAL DE MECANIQUE APPLIQUEE (S.I.G.M.A.). Dec. 1. 1947. No 31703. Convention date, Nov. 29 1946. [Class 110(iii)] The turbines 1, 2 can be worked either in series or in parallel. For series working, the compressor 5 is disconnected. The air compressed in low and high pressure compressors 3, 4 is heated in combustion chambers 10 and delivered to turbine 1. The exhaust from turbine 2 goes to a propulsion nozzle 16. For parallel working, the compressor 5 is coupled by a clutch 23, and the valve 15 connects conduits 14a and 28 so that the compressor 3 delivers air to the two compressors 4, 5. Air from the compressor 5 is heated in combustion chambers 25 and passes to turbine 2. The exhausts of the two turbines go to a collector 31 and thence by a conduit 33 to a propulsion nozzle. In series working, some of the air from compressor 3 passes through valve 15 to a conduit 14b and thence to a propulsion nozzle. Part of the working fluid tapped between the two turbines may also pass through valve 19 to the same nozzle. The compressor 4 and combustion chambers 10 may be replaced by a 'free-piston generator which is charged by the compressor 3 either from its delivery or from an intermediate tapping. The free-piston generator may take in atmospheric air and supply the whole of the working fluid for series working; the whole delivery of the compressor 3 being sent through the conduit 14b to a propulsion nozzle. The nozzles fed by the conduits 14b, 33 may be mounted on a helicopter or rotary wing.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR629920X | 1946-11-29 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB629920A true GB629920A (en) | 1949-09-30 |
Family
ID=8990712
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB31703/47A Expired GB629920A (en) | 1946-11-29 | 1947-12-01 | Improvements in jet propulsion plants, in particular for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB629920A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2747367A (en) * | 1950-03-21 | 1956-05-29 | United Aircraft Corp | Gas turbine power plant supporting structure |
| WO2019241898A1 (en) * | 2018-06-21 | 2019-12-26 | Envita Management & Development Gmbh | Gas turbine and method for operating a gas turbine |
-
1947
- 1947-12-01 GB GB31703/47A patent/GB629920A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2747367A (en) * | 1950-03-21 | 1956-05-29 | United Aircraft Corp | Gas turbine power plant supporting structure |
| WO2019241898A1 (en) * | 2018-06-21 | 2019-12-26 | Envita Management & Development Gmbh | Gas turbine and method for operating a gas turbine |
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