US3684857A - Air intakes - Google Patents
Air intakes Download PDFInfo
- Publication number
- US3684857A US3684857A US110973A US3684857DA US3684857A US 3684857 A US3684857 A US 3684857A US 110973 A US110973 A US 110973A US 3684857D A US3684857D A US 3684857DA US 3684857 A US3684857 A US 3684857A
- Authority
- US
- United States
- Prior art keywords
- air
- air intake
- outer casing
- engine
- leading edge
- 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 - Lifetime
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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
- F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
Definitions
- ABSTRACT A gas turbine engine air intake designed to prevent ingestion into the engine of a substantial proportion of [21] Appl' 110373 any ice or slush present in the incoming air.
- the air in- 7 take comprises a central bullet and an outer casing 30 F i li i priority Data defining an annular passage therebetween through a which air flows to the engine compressor.
- the central Feb. 5, Great Blltaln bullet is enlarged at upstream end to a mushroom shape whose outer periphery lies upstream of and is at 1.8- CI.
- the present invention relates to an improved construction of air intake for a gas turbine powerplant wherein a substantial proportion of any ice or slush present in the air is not ingested.
- an air intake for a gas turbine engine comprising an outer casing having a leading edge, a central bullet having an upstream end portion which is enlarged, an annular passage defined between said central bullet and said outer casing and adapted to receive a flow therethrough of air in a determined direction, said enlarged portion having an outer periphery which is forward of the leading edge of the outer casing and every point on which lies a greater distance from the central axis of the intake than its corresponding point in the same axial plane on the leading edge of the outer casmg.
- the enlarged portion of the nose bullet is of circular cross-section and its upstream surface is convex so as to form a dome.
- the words upstream and downstream in this context refer to the direction in which the air flows through the intake.
- Means are preferably provided for heating the surfaces of the intake which are exposed to the air flow.
- FIG. 1 is a part sectional side elevation of a gas turbine engine fitted with an air intake designed according to the invention.
- FIG. 2 is a longitudinal section of an air intake according to the invention.
- the gas turbine engine 1 in FIG. 1 includes compressor system 2, a combustion system 3 and a turbine system 4 all in flow series as shown and surrounded by an engine cowl 25.
- An air intake is attached to the compressor system and profiled to blend with the engine cowl.
- the air intake 11 comprises a central bullet 12 and an outer casing 13 havinginner and outer walls, 14 and 15 respectively, meeting at the leading edge of the outer casing which throughout the specification should be taken as the most upstream point 16 of the casing.
- the outer casing is supported 7 from the central bullet by struts 17 to define an annular passage 18 therebetween.
- the direction of. air entering the air intake is indicated by arrows 19.
- the central bullet 12 is enlarged at its upstream end into a shape, which will hereinafter be referred to as the mushroom 21, which is of circular cross-section and of which the upstream surface is convex to form a dome.
- the outer periphery 22 of the mushroom 21 lies upstream of the leading edge 16 of the outer casing 13 and every point on the outer periphery 22 lies at a greater distance from the central axis 23 of the air intake than its corresponding point in the same axial plane on the leading edge 16 of the outer casing.
- the surfaces are heated by electric resistance coils 26 placed on the surfaces and held in position by a matting 27.
- the matting 27 which may be of rubber or plastics material is bonded to the air intake surfaces.
- the air intake shown in this example is for a gas turbine powerplant mounted on top of the fuselage of a helicopter and is of particular advantage where ice and slush formed on top of the fuselage forward of the powerplant breaks away and is urged towards the air intake. If two powerplants each fitted with this air intake are mounted side by side a gutter could be formed between the powerplants to facilitate the easy removal of ice and slush deflected by the mushrooms to the space between them.
- an air intake constructed according to the invention would in operation also remove a substantial proportion .of other particulate matter, for example sand, from the incoming air.
- An air intake for a gas turbine engine comprising an outer casing having a leading edge, a central bullet having an upstream end portion which is enlarged, an annular passage defined between said central bullet and said outer casing and adapted to receive a flow therethrough of air in a determined direction, said enlarged portion having an upstream surface which is convex forming a dome and having an outer periphery which is forward of the leading edge of the outer casing and every point on said periphery lies at a greater distance from the central axis of the intake than its corresponding point in the same axial: plane on the leading edge of the outer casing.
- heating means comprise electrical resistance coils which are held in position on said surfaces by a matting material which is bonded to said surfaces.
Abstract
A gas turbine engine air intake designed to prevent ingestion into the engine of a substantial proportion of any ice or slush present in the incoming air. The air intake comprises a central bullet and an outer casing defining an annular passage therebetween through which air flows to the engine compressor. The central bullet is enlarged at its upstream end to a mushroom shape whose outer periphery lies upstream of and is at a greater radius than the leading edge of the outer casing. In operation the ice and slush is deflected by reason of its greater momentum around the outside of the engine cowl and out of the path of the air drawn into the annular passage.
Description
United States Patent Morley et al. [451 Aug. 15, 1972 AIR INTAKES [56] References Cited [72] Inventors: Frederick William Walton Morley, UNITED STATES PATENTS Derby; George Henry Bennett, Lon- 3,534,548 10/1970 Connors ..60/39.09 P v don; Richard George Harvey, 3,063,031 11/ 1962 Edwards et al. ..2l9/202 X Wiltshire; Alan Wilson, Hampshire, 2,791,668 5/1957 Cowdrey et a1 ..219/202 X all Of Engl Primary Examiner-C. L. Albritton [73] Assignee: Rolbnoyce Limited, Derby Em Attorney-Stevens, Davis, Miller & Mosher gland [57] ABSTRACT [22] Filed: Jan. 29, 1971 A gas turbine engine air intake designed to prevent ingestion into the engine of a substantial proportion of [21] Appl' 110373 any ice or slush present in the incoming air. The air in- 7 take comprises a central bullet and an outer casing 30 F i li i priority Data defining an annular passage therebetween through a which air flows to the engine compressor. The central Feb. 5, Great Blltaln bullet is enlarged at upstream end to a mushroom shape whose outer periphery lies upstream of and is at 1.8- CI. D, P a greater radius than the leading ,edge of the outer as- [51] Int. Cl. ..H05b U00 ing. In operation the ice and slush is deflected by [58] Field of Search ..219/200, 202, 528, 529, 526, reason of its greater momentum around the outside of the engine cowl and out of the path of the air drawn 137/ 15, 1 into the annular passage.
4 Claims, 2 Drawing Figures PATENTEDAus 1 5 L972 34684; 857
sum 1 [1F 2 AIR INTAKES In operation of gas turbine powerplants problems arise due to the ingestion into the engine of ice and slush with the incoming air. Ice and slush can cause a flame out of the combustion system of the engine.
The present invention relates to an improved construction of air intake for a gas turbine powerplant wherein a substantial proportion of any ice or slush present in the air is not ingested.
According to the invention there is provided an air intake for a gas turbine engine comprising an outer casing having a leading edge, a central bullet having an upstream end portion which is enlarged, an annular passage defined between said central bullet and said outer casing and adapted to receive a flow therethrough of air in a determined direction, said enlarged portion having an outer periphery which is forward of the leading edge of the outer casing and every point on which lies a greater distance from the central axis of the intake than its corresponding point in the same axial plane on the leading edge of the outer casmg.
In a preferred form the enlarged portion of the nose bullet is of circular cross-section and its upstream surface is convex so as to form a dome. The words upstream and downstream in this context refer to the direction in which the air flows through the intake.
Means are preferably provided for heating the surfaces of the intake which are exposed to the air flow.
An embodiment of the invention will now be described by way of example only with reference to the accompanying drawings in which:
FIG. 1 is a part sectional side elevation of a gas turbine engine fitted with an air intake designed according to the invention.
FIG. 2 is a longitudinal section of an air intake according to the invention. I
The gas turbine engine 1 in FIG. 1 includes compressor system 2, a combustion system 3 and a turbine system 4 all in flow series as shown and surrounded by an engine cowl 25. An air intake is attached to the compressor system and profiled to blend with the engine cowl.
Referring now to FIG. 2, the air intake 11 comprises a central bullet 12 and an outer casing 13 havinginner and outer walls, 14 and 15 respectively, meeting at the leading edge of the outer casing which throughout the specification should be taken as the most upstream point 16 of the casing. The outer casing is supported 7 from the central bullet by struts 17 to define an annular passage 18 therebetween. The direction of. air entering the air intake is indicated by arrows 19.
The central bullet 12 is enlarged at its upstream end into a shape, which will hereinafter be referred to as the mushroom 21, which is of circular cross-section and of which the upstream surface is convex to form a dome. The outer periphery 22 of the mushroom 21 lies upstream of the leading edge 16 of the outer casing 13 and every point on the outer periphery 22 lies at a greater distance from the central axis 23 of the air intake than its corresponding point in the same axial plane on the leading edge 16 of the outer casing.
In operation the incoming air strikes the dome 24 of the mushroom and flows outwards towards the outer essayist: fi e til ailmllg s g fi. fc fi slush mixed with the air deflected by the mushroom is by reason of its greater momentum carried out of the path of the air drawn into the annular passage. This ice and slush passes round the outside of the engine cowl 25 or strikes the outer wall 15 of the outer casing and slides off around the engine cowl.
To prevent ice forming on the surfaces of the air intake the surfaces are heated by electric resistance coils 26 placed on the surfaces and held in position by a matting 27. The matting 27 which may be of rubber or plastics material is bonded to the air intake surfaces.
The air intake shown in this example is for a gas turbine powerplant mounted on top of the fuselage of a helicopter and is of particular advantage where ice and slush formed on top of the fuselage forward of the powerplant breaks away and is urged towards the air intake. If two powerplants each fitted with this air intake are mounted side by side a gutter could be formed between the powerplants to facilitate the easy removal of ice and slush deflected by the mushrooms to the space between them.
It will be appreciated that an air intake constructed according to the invention would in operation also remove a substantial proportion .of other particulate matter, for example sand, from the incoming air.
We claim:
1. An air intake for a gas turbine engine comprising an outer casing having a leading edge, a central bullet having an upstream end portion which is enlarged, an annular passage defined between said central bullet and said outer casing and adapted to receive a flow therethrough of air in a determined direction, said enlarged portion having an upstream surface which is convex forming a dome and having an outer periphery which is forward of the leading edge of the outer casing and every point on said periphery lies at a greater distance from the central axis of the intake than its corresponding point in the same axial: plane on the leading edge of the outer casing.
2. An air intake according to claim 1, in which the enlarged portion of the central bullet is of circular cross-section.
3. An air intake according to claim 1, additionally comprising means for heating surfaces of the air intake which are exposed to a flow of air.
4. An air intake according to claim 3 in which said heating means comprise electrical resistance coils which are held in position on said surfaces by a matting material which is bonded to said surfaces.
Claims (4)
1. An air intake for a gas turbine engine comprising an outer casing having a leading edge, a central bullet having an upstream end portion which is enlarged, an annular passage defined between said central bullet and said outer casing and adapted to receive a flow therethrough of air in a determined direction, said enlarged portion having an upstream surface which is convex forming a dome and having an outer periphery which is forward of the leading edge of the outer casing and every point on said periphery lies at a greater distance from the central axis of the intake than its corresponding point in the same axial plane on the leading edge of the outer casing.
2. An air intake according to claim 1, in which the enlarged portion of the central bullet is of circular cross-section.
3. An air intake according to claim 1, additionally comprising means for heating surfaces of the air intake which are exposed to a flow of air.
4. An air intake according to claim 3 in which said heating means comprise electrical resistance coils which are held in position on said surfaces by a matting material which is bonded to said surfaces.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB547670 | 1970-02-05 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3684857A true US3684857A (en) | 1972-08-15 |
Family
ID=9796916
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US110973A Expired - Lifetime US3684857A (en) | 1970-02-05 | 1971-01-29 | Air intakes |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US3684857A (en) |
| DE (1) | DE2103035C3 (en) |
| FR (1) | FR2079257B1 (en) |
| GB (1) | GB1328993A (en) |
Cited By (49)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3103603A1 (en) * | 1980-02-09 | 1982-01-07 | Rolls-Royce Ltd., London | AIR INLET FOR A GAS TURBINE ENGINE |
| DE3104005A1 (en) * | 1980-02-09 | 1982-01-14 | Rolls-Royce Ltd., London | AIR INLET FOR A GAS TURBINE ENGINE |
| WO2006059987A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Particle separator for tip turbine engine |
| US20070101696A1 (en) * | 2005-11-09 | 2007-05-10 | Pratt & Whitney Canada Corp. | Gas turbine engine with power transfer and method |
| US20080014078A1 (en) * | 2004-12-01 | 2008-01-17 | Suciu Gabriel L | Ejector Cooling of Outer Case for Tip Turbine Engine |
| US20080093174A1 (en) * | 2004-12-01 | 2008-04-24 | Suciu Gabriel L | Tip Turbine Engine with a Heat Exchanger |
| US20080124211A1 (en) * | 2004-12-01 | 2008-05-29 | Suciu Gabriel L | Diffuser Aspiration For A Tip Turbine Engine |
| US20090071162A1 (en) * | 2004-12-01 | 2009-03-19 | Suciu Gabriel L | Peripheral combustor for tip turbine engine |
| US20090142184A1 (en) * | 2004-12-01 | 2009-06-04 | Roberge Gary D | Vectoring transition duct for turbine engine |
| US20090145136A1 (en) * | 2004-12-01 | 2009-06-11 | Norris James W | Tip turbine engine with multiple fan and turbine stages |
| US20090148273A1 (en) * | 2004-12-01 | 2009-06-11 | Suciu Gabriel L | Compressor inlet guide vane for tip turbine engine and corresponding control method |
| US20090155079A1 (en) * | 2004-12-01 | 2009-06-18 | Suciu Gabriel L | Stacked annular components for turbine engines |
| US20090232650A1 (en) * | 2004-12-01 | 2009-09-17 | Gabriel Suciu | Tip turbine engine and corresponding operating method |
| US7607286B2 (en) | 2004-12-01 | 2009-10-27 | United Technologies Corporation | Regenerative turbine blade and vane cooling for a tip turbine engine |
| US7631480B2 (en) | 2004-12-01 | 2009-12-15 | United Technologies Corporation | Modular tip turbine engine |
| US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
| US7874163B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Starter generator system for a tip turbine engine |
| US7874802B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Tip turbine engine comprising turbine blade clusters and method of assembly |
| US7878762B2 (en) | 2004-12-01 | 2011-02-01 | United Technologies Corporation | Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor |
| US7882694B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Variable fan inlet guide vane assembly for gas turbine engine |
| US7883315B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan rotor of a tip turbine engine |
| US7883314B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan-turbine rotor of a tip turbine engine |
| US7882695B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Turbine blow down starter for turbine engine |
| US7887296B2 (en) | 2004-12-01 | 2011-02-15 | United Technologies Corporation | Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine |
| US7927075B2 (en) | 2004-12-01 | 2011-04-19 | United Technologies Corporation | Fan-turbine rotor assembly for a tip turbine engine |
| US7934902B2 (en) | 2004-12-01 | 2011-05-03 | United Technologies Corporation | Compressor variable stage remote actuation for turbine engine |
| US7937927B2 (en) | 2004-12-01 | 2011-05-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
| US7959532B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Hydraulic seal for a gearbox of a tip turbine engine |
| US7959406B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Close coupled gearbox assembly for a tip turbine engine |
| US7976273B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Tip turbine engine support structure |
| US7976272B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Inflatable bleed valve for a turbine engine |
| US8024931B2 (en) | 2004-12-01 | 2011-09-27 | United Technologies Corporation | Combustor for turbine engine |
| US8033094B2 (en) | 2004-12-01 | 2011-10-11 | United Technologies Corporation | Cantilevered tip turbine engine |
| US8033092B2 (en) | 2004-12-01 | 2011-10-11 | United Technologies Corporation | Tip turbine engine integral fan, combustor, and turbine case |
| US8061968B2 (en) | 2004-12-01 | 2011-11-22 | United Technologies Corporation | Counter-rotating compressor case and assembly method for tip turbine engine |
| US8083030B2 (en) | 2004-12-01 | 2011-12-27 | United Technologies Corporation | Gearbox lubrication supply system for a tip engine |
| US8096753B2 (en) | 2004-12-01 | 2012-01-17 | United Technologies Corporation | Tip turbine engine and operating method with reverse core airflow |
| US8152469B2 (en) | 2004-12-01 | 2012-04-10 | United Technologies Corporation | Annular turbine ring rotor |
| US8365511B2 (en) | 2004-12-01 | 2013-02-05 | United Technologies Corporation | Tip turbine engine integral case, vane, mount and mixer |
| US8561383B2 (en) | 2004-12-01 | 2013-10-22 | United Technologies Corporation | Turbine engine with differential gear driven fan and compressor |
| US8641367B2 (en) | 2004-12-01 | 2014-02-04 | United Technologies Corporation | Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method |
| US8757959B2 (en) | 2004-12-01 | 2014-06-24 | United Technologies Corporation | Tip turbine engine comprising a nonrotable compartment |
| US8807936B2 (en) | 2004-12-01 | 2014-08-19 | United Technologies Corporation | Balanced turbine rotor fan blade for a tip turbine engine |
| US8967945B2 (en) | 2007-05-22 | 2015-03-03 | United Technologies Corporation | Individual inlet guide vane control for tip turbine engine |
| US9109537B2 (en) | 2004-12-04 | 2015-08-18 | United Technologies Corporation | Tip turbine single plane mount |
| US9845727B2 (en) | 2004-12-01 | 2017-12-19 | United Technologies Corporation | Tip turbine engine composite tailcone |
| US9857017B2 (en) * | 2015-10-30 | 2018-01-02 | Akron Brass Company | Debris diverting inlet |
| CN109339948A (en) * | 2018-11-23 | 2019-02-15 | 江西洪都航空工业集团有限责任公司 | Bullet gas-turbine unit inlet duct |
| RU218689U1 (en) * | 2023-03-03 | 2023-06-06 | Владимир Викторович Брокерт | Protection device for aircraft gas turbine engines from birds |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2791668A (en) * | 1951-08-21 | 1957-05-07 | Napier & Son Ltd | Electrically heated de-icing or antifreezing apparatus |
| US3063031A (en) * | 1959-12-28 | 1962-11-06 | Gen Motors Corp | Electrical aircraft heater |
| US3534548A (en) * | 1969-06-30 | 1970-10-20 | Avco Corp | Separator apparatus for engine air inlets |
-
1971
- 1971-01-22 DE DE2103035A patent/DE2103035C3/en not_active Expired
- 1971-01-29 US US110973A patent/US3684857A/en not_active Expired - Lifetime
- 1971-02-04 FR FR7103692A patent/FR2079257B1/fr not_active Expired
- 1971-04-23 GB GB547670A patent/GB1328993A/en not_active Expired
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2791668A (en) * | 1951-08-21 | 1957-05-07 | Napier & Son Ltd | Electrically heated de-icing or antifreezing apparatus |
| US3063031A (en) * | 1959-12-28 | 1962-11-06 | Gen Motors Corp | Electrical aircraft heater |
| US3534548A (en) * | 1969-06-30 | 1970-10-20 | Avco Corp | Separator apparatus for engine air inlets |
Cited By (71)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3103603A1 (en) * | 1980-02-09 | 1982-01-07 | Rolls-Royce Ltd., London | AIR INLET FOR A GAS TURBINE ENGINE |
| DE3104005A1 (en) * | 1980-02-09 | 1982-01-14 | Rolls-Royce Ltd., London | AIR INLET FOR A GAS TURBINE ENGINE |
| US4389227A (en) * | 1980-02-09 | 1983-06-21 | Rolls-Royce Limited | Gas turbine engine air intake |
| US4493185A (en) * | 1980-02-09 | 1985-01-15 | Rolls-Royce Limited | Gas turbine engine air intake |
| US7959406B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Close coupled gearbox assembly for a tip turbine engine |
| US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
| US20080093174A1 (en) * | 2004-12-01 | 2008-04-24 | Suciu Gabriel L | Tip Turbine Engine with a Heat Exchanger |
| US20080124211A1 (en) * | 2004-12-01 | 2008-05-29 | Suciu Gabriel L | Diffuser Aspiration For A Tip Turbine Engine |
| US20090071162A1 (en) * | 2004-12-01 | 2009-03-19 | Suciu Gabriel L | Peripheral combustor for tip turbine engine |
| US20090142184A1 (en) * | 2004-12-01 | 2009-06-04 | Roberge Gary D | Vectoring transition duct for turbine engine |
| US20090145136A1 (en) * | 2004-12-01 | 2009-06-11 | Norris James W | Tip turbine engine with multiple fan and turbine stages |
| US7976273B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Tip turbine engine support structure |
| US20090155079A1 (en) * | 2004-12-01 | 2009-06-18 | Suciu Gabriel L | Stacked annular components for turbine engines |
| US20090232650A1 (en) * | 2004-12-01 | 2009-09-17 | Gabriel Suciu | Tip turbine engine and corresponding operating method |
| US7607286B2 (en) | 2004-12-01 | 2009-10-27 | United Technologies Corporation | Regenerative turbine blade and vane cooling for a tip turbine engine |
| US7631485B2 (en) | 2004-12-01 | 2009-12-15 | United Technologies Corporation | Tip turbine engine with a heat exchanger |
| US7631480B2 (en) | 2004-12-01 | 2009-12-15 | United Technologies Corporation | Modular tip turbine engine |
| US7976272B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Inflatable bleed valve for a turbine engine |
| US7854112B2 (en) | 2004-12-01 | 2010-12-21 | United Technologies Corporation | Vectoring transition duct for turbine engine |
| US7874163B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Starter generator system for a tip turbine engine |
| US7874802B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Tip turbine engine comprising turbine blade clusters and method of assembly |
| US7980054B2 (en) | 2004-12-01 | 2011-07-19 | United Technologies Corporation | Ejector cooling of outer case for tip turbine engine |
| US7882694B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Variable fan inlet guide vane assembly for gas turbine engine |
| US7883315B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan rotor of a tip turbine engine |
| US7883314B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan-turbine rotor of a tip turbine engine |
| US7882695B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Turbine blow down starter for turbine engine |
| US7887296B2 (en) | 2004-12-01 | 2011-02-15 | United Technologies Corporation | Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine |
| US7921635B2 (en) | 2004-12-01 | 2011-04-12 | United Technologies Corporation | Peripheral combustor for tip turbine engine |
| US7921636B2 (en) | 2004-12-01 | 2011-04-12 | United Technologies Corporation | Tip turbine engine and corresponding operating method |
| US10760483B2 (en) | 2004-12-01 | 2020-09-01 | Raytheon Technologies Corporation | Tip turbine engine composite tailcone |
| US7927075B2 (en) | 2004-12-01 | 2011-04-19 | United Technologies Corporation | Fan-turbine rotor assembly for a tip turbine engine |
| US7934902B2 (en) | 2004-12-01 | 2011-05-03 | United Technologies Corporation | Compressor variable stage remote actuation for turbine engine |
| US7937927B2 (en) | 2004-12-01 | 2011-05-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
| US7959532B2 (en) | 2004-12-01 | 2011-06-14 | United Technologies Corporation | Hydraulic seal for a gearbox of a tip turbine engine |
| WO2006059987A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Particle separator for tip turbine engine |
| US20110142601A1 (en) * | 2004-12-01 | 2011-06-16 | Suciu Gabriel L | Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method |
| US20090148273A1 (en) * | 2004-12-01 | 2009-06-11 | Suciu Gabriel L | Compressor inlet guide vane for tip turbine engine and corresponding control method |
| US20080014078A1 (en) * | 2004-12-01 | 2008-01-17 | Suciu Gabriel L | Ejector Cooling of Outer Case for Tip Turbine Engine |
| US7878762B2 (en) | 2004-12-01 | 2011-02-01 | United Technologies Corporation | Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor |
| US20110200424A1 (en) * | 2004-12-01 | 2011-08-18 | Gabriel Suciu | Counter-rotating gearbox for tip turbine engine |
| US8024931B2 (en) | 2004-12-01 | 2011-09-27 | United Technologies Corporation | Combustor for turbine engine |
| US8033094B2 (en) | 2004-12-01 | 2011-10-11 | United Technologies Corporation | Cantilevered tip turbine engine |
| US8033092B2 (en) | 2004-12-01 | 2011-10-11 | United Technologies Corporation | Tip turbine engine integral fan, combustor, and turbine case |
| US8061968B2 (en) | 2004-12-01 | 2011-11-22 | United Technologies Corporation | Counter-rotating compressor case and assembly method for tip turbine engine |
| US8083030B2 (en) | 2004-12-01 | 2011-12-27 | United Technologies Corporation | Gearbox lubrication supply system for a tip engine |
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| US7690186B2 (en) * | 2005-11-09 | 2010-04-06 | Pratt & Whitney Canada Corp. | Gas turbine engine including apparatus to transfer power between multiple shafts |
| US20070101696A1 (en) * | 2005-11-09 | 2007-05-10 | Pratt & Whitney Canada Corp. | Gas turbine engine with power transfer and method |
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| US9857017B2 (en) * | 2015-10-30 | 2018-01-02 | Akron Brass Company | Debris diverting inlet |
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Also Published As
| Publication number | Publication date |
|---|---|
| DE2103035A1 (en) | 1971-08-26 |
| DE2103035B2 (en) | 1974-08-01 |
| DE2103035C3 (en) | 1975-03-27 |
| GB1328993A (en) | 1973-09-05 |
| FR2079257B1 (en) | 1975-06-06 |
| FR2079257A1 (en) | 1971-11-12 |
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