GB650661A - Jet reaction propulsion unit for aircraft - Google Patents
Jet reaction propulsion unit for aircraftInfo
- Publication number
- GB650661A GB650661A GB819/41A GB81941A GB650661A GB 650661 A GB650661 A GB 650661A GB 819/41 A GB819/41 A GB 819/41A GB 81941 A GB81941 A GB 81941A GB 650661 A GB650661 A GB 650661A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- compressor
- driven
- jet
- stage
- 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
- 238000006243 chemical reaction Methods 0.000 title abstract 2
- 238000002485 combustion reaction Methods 0.000 abstract 2
- 230000004048 modification Effects 0.000 abstract 1
- 238000012986 modification Methods 0.000 abstract 1
- 239000010705 motor oil Substances 0.000 abstract 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 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
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
650,661. Jet propulsion plant; axial-flow compressors. SOC. RATEAU, and ANXIONNAZ, R. Jan. 21,1941, No. 819. Convention date, Dec. 4, 1939. '[Classes 110(i) and 1l0(iii)] [Also in Group XXXIII] A jet reaction propulsion unit has a fore and aft casing with its inlet at the forward end arranged so that the velocity of the air is reduced on entry before reaching the blades of an axially arranged axial flow compressor. The compressor is driven either by a gas turbine 34 or by a piston engine, and the compressed gas may be heated by burners 31 or by the engine oil and water coolers or the exhaust of the turbine or engine. The compressor may have two stages, Fig. 15, each stage being driven by a separate turbine 46, 48, only part of the output of the first stage 40 passing to the second stage and the combustion chamber 32. In a further modification both stages are driven by the same turbine and the initial stage driven at a lower speed through reduction gearing.' The exhaust gas may be cooled by air admitted through the side inlet 36, Fig. 12. The turbine is started by the engine 64 or by injecting and burning air from compressed air bottles in the combustion chamber. To vary the operating conditions of the compressor a row of blading 65, Fig. 3a, may be held stationary by brakes 70 or may be freed to run idly. Adjustable deflecting blades can be fitted in the outlet to varying the. direction of the jet thrust, or for using the jet to brake the aircraft. Specifications 471,368 and 650,710 are referred to. Reference has been directed by the Comptroller to Specification 471.368.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR650661X | 1939-12-04 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB650661A true GB650661A (en) | 1951-02-28 |
Family
ID=9004117
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB819/41A Expired GB650661A (en) | 1939-12-04 | 1941-01-21 | Jet reaction propulsion unit for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB650661A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2148395A (en) * | 1983-10-24 | 1985-05-30 | Mannesmann Ag | Brakes for multistage compressors |
| EP1160432A1 (en) | 2000-05-31 | 2001-12-05 | Daniel Bregentzer | Gas turbine engine |
-
1941
- 1941-01-21 GB GB819/41A patent/GB650661A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2148395A (en) * | 1983-10-24 | 1985-05-30 | Mannesmann Ag | Brakes for multistage compressors |
| EP1160432A1 (en) | 2000-05-31 | 2001-12-05 | Daniel Bregentzer | Gas turbine engine |
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