GB716145A - Improvements in aircraft jet propulsion engines including a ducted fan - Google Patents
Improvements in aircraft jet propulsion engines including a ducted fanInfo
- Publication number
- GB716145A GB716145A GB440252A GB440252A GB716145A GB 716145 A GB716145 A GB 716145A GB 440252 A GB440252 A GB 440252A GB 440252 A GB440252 A GB 440252A GB 716145 A GB716145 A GB 716145A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- turbine
- jet propulsion
- prime mover
- duct
- 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
- F02K5/00—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
- F02K5/02—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan the engine being of the reciprocating-piston type
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
716,145. Jet propulsion plant: gas turbines. LAGELBAUER, E. Feb. 19, 1952, No. 4402/52. Class 110(3) An aircraft jet propulsion engine comprising a prime mover driving an air compressor part of the discharge of which is supplied to the prime mover and part direct to a jet propulsion nozzle and a second prime mover, driven by exhaust gases from the first prime mover, driving a ducted fan, has means for varying the ratio of the amount of air supplied to the first prime mover to that passing direct to the jet propulsion nozzle. Air compressed in a low pressure axial-flow compressor 16 is passed through a cooler 29 to a high pressure axial-flow compressor 17 which feeds a combustion chamber 18. The gases for this combustion chamber pass through a high pressure turbine 15 driving the compressors 16, 17 to a low pressure turbine 13 driving a ducted fan 11 which exhausts through a jet propulsion nozzle 33. A part of the compressed air from the low pressure compressor 16 is passed through a valve 23 and a duct 24 to cool the blades of a turbine 15 after which it is mixed with the turbine exhaust gases and used in the turbine 13. A valve 19 diverts another portion of air from the compressor 16 through a duct 20 direct to the propulsion nozzle 32. A heat exchanger 21 transfers heat from the turbine exhaust gases to this air. Compressed air from the outlet of the cooler 29 is passed through a valve 28 and duct 27 to the casing 31 around the turbine 13 to cool it. This air is then mixed with the air passing through the duct 20. By operation of the valves 19, 23 and 28 it is possible to control the output of the turbine 13 and the speed of the ducted fan 11 to the various conditions of flight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB440252A GB716145A (en) | 1952-02-19 | 1952-02-19 | Improvements in aircraft jet propulsion engines including a ducted fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB440252A GB716145A (en) | 1952-02-19 | 1952-02-19 | Improvements in aircraft jet propulsion engines including a ducted fan |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB716145A true GB716145A (en) | 1954-09-29 |
Family
ID=9776505
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB440252A Expired GB716145A (en) | 1952-02-19 | 1952-02-19 | Improvements in aircraft jet propulsion engines including a ducted fan |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB716145A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1057392B (en) * | 1954-11-04 | 1959-05-14 | Garrett Corp | Propulsion system for an aircraft |
| GB2249140A (en) * | 1990-08-30 | 1992-04-29 | S & C Thermofluids Ltd | Noise suppression in gas turbine engine |
| GB2272025A (en) * | 1992-10-28 | 1994-05-04 | Snecma | Air heating system for turbojet bypass engines. |
-
1952
- 1952-02-19 GB GB440252A patent/GB716145A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1057392B (en) * | 1954-11-04 | 1959-05-14 | Garrett Corp | Propulsion system for an aircraft |
| GB2249140A (en) * | 1990-08-30 | 1992-04-29 | S & C Thermofluids Ltd | Noise suppression in gas turbine engine |
| GB2249140B (en) * | 1990-08-30 | 1994-12-07 | S & C Thermofluids Ltd | Aircraft engine noise suppression |
| GB2272025A (en) * | 1992-10-28 | 1994-05-04 | Snecma | Air heating system for turbojet bypass engines. |
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