GB986878A - Improvements in or relating to gas turbine engines - Google Patents
Improvements in or relating to gas turbine enginesInfo
- Publication number
- GB986878A GB986878A GB767464A GB767464A GB986878A GB 986878 A GB986878 A GB 986878A GB 767464 A GB767464 A GB 767464A GB 767464 A GB767464 A GB 767464A GB 986878 A GB986878 A GB 986878A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- struts
- air intake
- conduit
- annular
- 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
Abstract
986,878. Gas turbine engines. ROLLSROYCE Ltd. Feb. 24, 1964, No. 7674/64. Addition to 879,621. Heading FlG. A gas turbine engine comprises an air intake across which extend substantially radially a plurality of angularly spaced apart struts, a wall of the air intake forming the radially inner wall of an annular conduit which extends from adjacent the struts to the leading edge of the air intake. The engine is provided with ducts means by which air which has been compressed by compressor means of the engine and heated thereby is passed to passageways in the interiors of the struts, the heated air first passing radially inwardly through the passageways and then radially outwardly through adjacent passageways in the struts which are thereby heated. The heated air which has passed through the struts is supplied to the annular conduit so as to effect heating of the leading edge of the air intake. A portion of the air intake 11 of a gas turbine engine is shown in Fig. 1, the intake being defined by a wall 13 which constitutes the radially inner wall of an annular conduit 14. Air under pressure from the engine compressor is supplied through a duct 20 to two axially spaced annular manifolds 21, 22 thence passing through tubes 23 which extend into struts 12 which extend radially across the air intake duct 11. The air discharging from the tubes flows radially outwardly through the struts adjacent the leading and trailing edges thereof into an annular manifold 24 within which the manifolds 21, 22 are disposed. The air then passes through aligned ducts 26, 28 into the annular conduit 14 thus heating the air intake. The air from the conduit 14 discharges at 16 and then flows through an annular passage 31 and is utilised for heating other parts of the engine. In a second embodiment the air from the conduit 14 is discharged to atmosphere whilst in a third embodiment the air from the conduit 14 is caused to flow through an adjacent annular passage and back into the air intake 11.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB767464A GB986878A (en) | 1964-02-24 | 1964-02-24 | Improvements in or relating to gas turbine engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB767464A GB986878A (en) | 1964-02-24 | 1964-02-24 | Improvements in or relating to gas turbine engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB986878A true GB986878A (en) | 1965-03-24 |
Family
ID=9837619
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB767464A Expired GB986878A (en) | 1964-02-24 | 1964-02-24 | Improvements in or relating to gas turbine engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB986878A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2224779A (en) * | 1988-10-03 | 1990-05-16 | Gen Electric | Aircraft engine inlet cowl anti-icing system |
| FR2771776A1 (en) * | 1997-12-02 | 1999-06-04 | Aerospatiale | HOT AIR DISCHARGE DEVICE FOR REACTION ENGINE AIR INTAKE COVER WITH DEFROSTING CIRCUIT |
| US6241189B1 (en) * | 1997-11-21 | 2001-06-05 | Aerospatiale Societe Nationale Industrielle | Protective device for a jet engine air inlet cowl equipped with a deicing system |
| WO2014167259A1 (en) * | 2013-04-11 | 2014-10-16 | Snecma | Device for deicing an aeronautical turbomachine separator |
| EP3287622A1 (en) * | 2016-08-26 | 2018-02-28 | Honeywell International Inc. | Anti-icing exhaust system |
| FR3131939A1 (en) * | 2022-01-18 | 2023-07-21 | Safran Aircraft Engines | AXIAL TURBOMACHINE SPLITTER INCLUDING DEFROST AIR FLOW PASSAGE EXTENDING TO RECTIFIER |
-
1964
- 1964-02-24 GB GB767464A patent/GB986878A/en not_active Expired
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2224779A (en) * | 1988-10-03 | 1990-05-16 | Gen Electric | Aircraft engine inlet cowl anti-icing system |
| GB2224779B (en) * | 1988-10-03 | 1993-03-31 | Gen Electric | Aircraft engine inlet cowl anti-icing system |
| US6241189B1 (en) * | 1997-11-21 | 2001-06-05 | Aerospatiale Societe Nationale Industrielle | Protective device for a jet engine air inlet cowl equipped with a deicing system |
| FR2771776A1 (en) * | 1997-12-02 | 1999-06-04 | Aerospatiale | HOT AIR DISCHARGE DEVICE FOR REACTION ENGINE AIR INTAKE COVER WITH DEFROSTING CIRCUIT |
| EP0921293A1 (en) * | 1997-12-02 | 1999-06-09 | Aerospatiale Societe Nationale Industrielle | Hot air exhaust device for a jet engine air intake fairing with de-icing circuit |
| US6131855A (en) * | 1997-12-02 | 2000-10-17 | Societe Nationale Industrielle Et Aerospatiale | Device for removing hot air for a jet engine air inlet cowl with a de-icing circuit |
| WO2014167259A1 (en) * | 2013-04-11 | 2014-10-16 | Snecma | Device for deicing an aeronautical turbomachine separator |
| FR3004485A1 (en) * | 2013-04-11 | 2014-10-17 | Snecma | DEVICE FOR DEFROSTING AN AERONAUTICAL TURBOMACHINE SEPARATION SPOUT |
| CN105102767B (en) * | 2013-04-11 | 2017-11-07 | 斯内克马公司 | The separator front end deicer of aero-turbine |
| US10138755B2 (en) | 2013-04-11 | 2018-11-27 | Safran Aircraft Engines | Device for deicing a separator nose of an aviation turbine engine |
| EP3287622A1 (en) * | 2016-08-26 | 2018-02-28 | Honeywell International Inc. | Anti-icing exhaust system |
| US10221765B2 (en) | 2016-08-26 | 2019-03-05 | Honeywell International Inc. | Anti-icing exhaust system |
| FR3131939A1 (en) * | 2022-01-18 | 2023-07-21 | Safran Aircraft Engines | AXIAL TURBOMACHINE SPLITTER INCLUDING DEFROST AIR FLOW PASSAGE EXTENDING TO RECTIFIER |
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