GB592091A - Improvements in or relating to gas turbine power plants for aircraft - Google Patents
Improvements in or relating to gas turbine power plants for aircraftInfo
- Publication number
- GB592091A GB592091A GB2461644A GB2461644A GB592091A GB 592091 A GB592091 A GB 592091A GB 2461644 A GB2461644 A GB 2461644A GB 2461644 A GB2461644 A GB 2461644A GB 592091 A GB592091 A GB 592091A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- aperture
- intake
- duct
- gas 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
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
- 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
- F02C7/047—Heating to prevent icing
-
- 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
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Exhaust Silencers (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
592,091. Gas turbines. BRISTOL AEROPLANE CO., Ltd., OWNER, F. M., and MARCHANT, F. C. I. Dec. 8, 1944, No. 24616. [Class 110 (iii)] [Also in Group XXXIII] An aircraft gas turbine power plant has a single tubular intake duct which receives air from two sources, the air from one source entering in the general direction of the longitudinal axis of the duct and the air from the other source entering radially inwards around its peripheral edge. The air supply to the compressor 7 of a gas turbine power plant 5, Fig. 1, may be taken through the intake duct 11 from the opening 12 or from the aperture 17 in the upper trailing edge of the wing 6. The air from the aperture 17 is heated by passing over the engine which is enclosed in a shell 15. The source from which the compressor draws its air is controlled by the louvre-slats 18, a sleeve 19 on the intake-duct 11 and a grilled plate 20. The controls are interconnected and operated from the cockpit. When the louvre-slats 18 are fully open, the sleeve 19 closes the peripheral opening to the intake duct and the plate 20 closes the aperture 17. When the slats are fully closed, the sleeve 19 is withdrawn and hot air passes to the peripheral opening through the aperture 17. If desired, intermediate settings of the cockpit control may be arranged so as to allow part of the air supply to be taken by way of opening 12 and part by way of aperture 17. The control of the air supply may be used to prevent icing of the intake 12 at high altitudes, to maintain laminar flow over the wing or to prevent stones entering the intake at starting. When fuel tanks are installed in the wing, the shell 15 minimises the fire hazard as it forms a heat-insulating jacket for the exhaust pipe 10. If desired, the shell 15 may be dispensed with and the power plant mounted in a sealed compartment. Reference has been directed by the Comptroller to Specifications 579,657, [Group XXXIII], and 587,126.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US635914A US2508288A (en) | 1944-12-08 | 1945-12-19 | Gas turbine power plant for aircraft |
| FR936702D FR936702A (en) | 1944-12-08 | 1946-04-05 | Gas turbine aircraft engine enhancements |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB592091A true GB592091A (en) | 1947-09-08 |
Family
ID=1738516
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2461644A Expired GB592091A (en) | 1944-12-08 | 1944-12-08 | Improvements in or relating to gas turbine power plants for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB592091A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1121414B (en) * | 1958-07-24 | 1962-01-04 | Ernst Heinkel Flugzeugbau G M | Device for controlling additional air in a jet engine |
| DE1134555B (en) * | 1958-06-05 | 1962-08-09 | Gen Electric | Recoil engine for supersonic flight speed |
| WO1997046796A1 (en) * | 1996-05-31 | 1997-12-11 | Energieversorgung Halle Gmbh | Process and device for preheating suction air by waste heat in power engines |
-
1944
- 1944-12-08 GB GB2461644A patent/GB592091A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1134555B (en) * | 1958-06-05 | 1962-08-09 | Gen Electric | Recoil engine for supersonic flight speed |
| DE1121414B (en) * | 1958-07-24 | 1962-01-04 | Ernst Heinkel Flugzeugbau G M | Device for controlling additional air in a jet engine |
| WO1997046796A1 (en) * | 1996-05-31 | 1997-12-11 | Energieversorgung Halle Gmbh | Process and device for preheating suction air by waste heat in power engines |
| US6666026B2 (en) | 1996-05-31 | 2003-12-23 | Energieversorgung Halle Gmbh | Process for preheating suction air by waste heat in power engines |
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