GB877838A - Improvements relating to gas turbine engine air intakes - Google Patents
Improvements relating to gas turbine engine air intakesInfo
- Publication number
- GB877838A GB877838A GB2856759A GB2856759A GB877838A GB 877838 A GB877838 A GB 877838A GB 2856759 A GB2856759 A GB 2856759A GB 2856759 A GB2856759 A GB 2856759A GB 877838 A GB877838 A GB 877838A
- Authority
- GB
- United Kingdom
- Prior art keywords
- intake
- vanes
- boundary layer
- wing
- 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
Abstract
877,838. Control of boundary layer in aircraft. power plant. ROLLS-ROYCE Ltd. May 31, 1960 [Aug. 20, 1959], No. 28567/59. Class 4. [Also in Group XXVI] A gas turbine engine air intake for use in a swept wing aircraft comprises vanes, adjacent the inboard and outboard edges at the forward end of the intake, which extend in vertical planes with respect to the wing, fully across the intake. A pair of engines whose centre lines are marked 12, 13 have a common intake 14. The front ends of the engines are indicated at 12a, 13a. The intake 14, which is divided into two by a wall 15, contains four vanes 16, 17, 18, 19 each of which extends across the full height of the intake. Vanes 17, 19 suppress break away of the boundary layer when the airflow is upward into the wing, i.e. ground running conditions. During flight, the vane 16 suppresses break away of the boundary layer. When the engines are throttled back, there is an outflow set up on the swept back wing. The curvature of flow causes break away which is suppressed by a vane 18. Vanes 16 and 19 can be used in any gas turbine engine intake. The vanes 17, 18 are only necessary in a multiengined installation. A boundary layer bleed control channel 20 may be provided.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2856759A GB877838A (en) | 1959-08-20 | 1959-08-20 | Improvements relating to gas turbine engine air intakes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2856759A GB877838A (en) | 1959-08-20 | 1959-08-20 | Improvements relating to gas turbine engine air intakes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB877838A true GB877838A (en) | 1961-09-20 |
Family
ID=10277661
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2856759A Expired GB877838A (en) | 1959-08-20 | 1959-08-20 | Improvements relating to gas turbine engine air intakes |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB877838A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2259114A (en) * | 1991-08-28 | 1993-03-03 | Gen Electric | Aircraft engine nacelle profile |
| GB2259115A (en) * | 1991-08-28 | 1993-03-03 | Gen Electric | Aircraft engine nacelle profile |
| EA009545B1 (en) * | 2004-12-31 | 2008-02-28 | Эрбус Эспанья, С.Л. | Auxiliary power unit intake duct with aero-acoustic guide vanes |
| US8499874B2 (en) | 2009-05-12 | 2013-08-06 | Icr Turbine Engine Corporation | Gas turbine energy storage and conversion system |
| US8669670B2 (en) | 2010-09-03 | 2014-03-11 | Icr Turbine Engine Corporation | Gas turbine engine configurations |
| US8866334B2 (en) | 2010-03-02 | 2014-10-21 | Icr Turbine Engine Corporation | Dispatchable power from a renewable energy facility |
| US8984895B2 (en) | 2010-07-09 | 2015-03-24 | Icr Turbine Engine Corporation | Metallic ceramic spool for a gas turbine engine |
| US9051873B2 (en) | 2011-05-20 | 2015-06-09 | Icr Turbine Engine Corporation | Ceramic-to-metal turbine shaft attachment |
| US10094288B2 (en) | 2012-07-24 | 2018-10-09 | Icr Turbine Engine Corporation | Ceramic-to-metal turbine volute attachment for a gas turbine engine |
-
1959
- 1959-08-20 GB GB2856759A patent/GB877838A/en not_active Expired
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2259114A (en) * | 1991-08-28 | 1993-03-03 | Gen Electric | Aircraft engine nacelle profile |
| GB2259115A (en) * | 1991-08-28 | 1993-03-03 | Gen Electric | Aircraft engine nacelle profile |
| EA009545B1 (en) * | 2004-12-31 | 2008-02-28 | Эрбус Эспанья, С.Л. | Auxiliary power unit intake duct with aero-acoustic guide vanes |
| US8499874B2 (en) | 2009-05-12 | 2013-08-06 | Icr Turbine Engine Corporation | Gas turbine energy storage and conversion system |
| US8708083B2 (en) | 2009-05-12 | 2014-04-29 | Icr Turbine Engine Corporation | Gas turbine energy storage and conversion system |
| US8866334B2 (en) | 2010-03-02 | 2014-10-21 | Icr Turbine Engine Corporation | Dispatchable power from a renewable energy facility |
| US8984895B2 (en) | 2010-07-09 | 2015-03-24 | Icr Turbine Engine Corporation | Metallic ceramic spool for a gas turbine engine |
| US8669670B2 (en) | 2010-09-03 | 2014-03-11 | Icr Turbine Engine Corporation | Gas turbine engine configurations |
| US9051873B2 (en) | 2011-05-20 | 2015-06-09 | Icr Turbine Engine Corporation | Ceramic-to-metal turbine shaft attachment |
| US10094288B2 (en) | 2012-07-24 | 2018-10-09 | Icr Turbine Engine Corporation | Ceramic-to-metal turbine volute attachment for a gas turbine engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US2632295A (en) | Inlet ram for power plants | |
| GB1283042A (en) | Improvements relating to aircraft | |
| GB1480340A (en) | Aircraft | |
| GB924078A (en) | Aircraft | |
| GB877838A (en) | Improvements relating to gas turbine engine air intakes | |
| GB1397068A (en) | Aircraft | |
| GB1411601A (en) | Ducted fan gas turbine engine supported by an aircraft wing mainspar | |
| GB940849A (en) | Improvements in inlet for vertical take-off aircraft | |
| GB817507A (en) | Improvements in or relating to aircraft | |
| GB1228806A (en) | ||
| GB1024894A (en) | Improvements in aircraft jet-propulsion power-plants | |
| GB938459A (en) | Rotary-wing aircraft | |
| GB1076152A (en) | Improvements in aircraft power plants | |
| GB862032A (en) | Aircraft | |
| GB735065A (en) | Jet propelled aircraft | |
| GB1032274A (en) | Mounting of ducted fan turbine engines in the tail of an aircraft | |
| GB1364692A (en) | Thrust spoilers of ducted fan gas turbine engines | |
| GB1041048A (en) | Improvements in aircraft having jet-propulsion power-plants | |
| US2388806A (en) | Aircraft | |
| GB860497A (en) | Improvements relating to turbo-jet propulsion units in aircraft | |
| GB796400A (en) | Improvements relating to air intakes for aircraft power plant installations | |
| GB1401187A (en) | Helicopter engine intakes | |
| GB672917A (en) | Improvements in turbine propulsion units and aircraft fitted with same | |
| GB1302228A (en) | ||
| GB895861A (en) | Improvements relating to aircraft |