GB1228806A - - Google Patents
Info
- Publication number
- GB1228806A GB1228806A GB1228806DA GB1228806A GB 1228806 A GB1228806 A GB 1228806A GB 1228806D A GB1228806D A GB 1228806DA GB 1228806 A GB1228806 A GB 1228806A
- Authority
- GB
- United Kingdom
- Prior art keywords
- intake
- intakes
- air
- gas turbine
- turbine engine
- 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
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
1,228,806. Gas turbine engine air intakes. ROLLS-ROYCE Ltd. July 4, 1968, No.31964/68. Heading F1G. An aircraft gas turbine engine has an air inlet duct 6 with two intakes 8, 10, both intakes being open during normal cruise conditions but the intake 10 being closed during landing such that the air in at least part of the duct is accelerated to sonic velocity to reduce forward noise propagation. The intake 8 is of circular cross-section and is formed by a faired ring member attached to the engine housing by angularly spaced struts 20, the latter defining therebetween the generally annular intake 10. Closure members 12 are slidable between adjacent struts 20 under the control of jacks 18 so as to block the intake 10 during landing.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB3196468 | 1968-07-04 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1228806A true GB1228806A (en) | 1971-04-21 |
Family
ID=10331017
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1228806D Expired GB1228806A (en) | 1968-07-04 | 1968-07-04 |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1228806A (en) |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2250060A (en) * | 1990-11-16 | 1992-05-27 | Rolls Royce Plc | Gas turbine engine nacelle |
US5177957A (en) * | 1990-03-22 | 1993-01-12 | Mtu Motoren-Und Turbinen-Union Muchen Gmbh | Propfan turbine engine |
WO2008045051A3 (en) * | 2006-10-12 | 2009-06-18 | United Technologies Corp | Gas turbine nacelle comprising a passive boundary lazer bleed system and method of controlling turbulent airflow |
RU2490177C2 (en) * | 2011-09-21 | 2013-08-20 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования Иркутский государственный университет путей сообщения (ФГБОУ ВПО ИрГУПС) | Device to prevent ingress of foreign matters into engine |
RU2491208C2 (en) * | 2011-09-21 | 2013-08-27 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования Иркутский государственный университет путей сообщения (ФГБОУ ВПО ИрГУПС) | Device to protect angine against ingress of foreign objects |
RU2491209C2 (en) * | 2011-09-21 | 2013-08-27 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования Иркутский государственный университет путей сообщения (ФГБОУ ВПО ИрГУПС) | Device to protect angine against ingress of foreign objects |
US8839805B2 (en) | 2006-10-12 | 2014-09-23 | United Technologies Corporation | Passive boundary layer bleed system for nacelle inlet airflow control |
EP1988266B1 (en) * | 2007-04-24 | 2014-11-26 | United Technologies Corporation | Nacelle assembly having inlet airfoil for a gas turbine engine |
WO2020212226A1 (en) | 2019-04-17 | 2020-10-22 | Safran Aircraft Engines | Turbojet comprising a nacelle with an air intake for promoting a reverse thrust phase |
-
1968
- 1968-07-04 GB GB1228806D patent/GB1228806A/en not_active Expired
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5177957A (en) * | 1990-03-22 | 1993-01-12 | Mtu Motoren-Und Turbinen-Union Muchen Gmbh | Propfan turbine engine |
GB2250060A (en) * | 1990-11-16 | 1992-05-27 | Rolls Royce Plc | Gas turbine engine nacelle |
US5145126A (en) * | 1990-11-16 | 1992-09-08 | Rolls-Royce Plc | Engine nacelle |
GB2250060B (en) * | 1990-11-16 | 1995-03-01 | Rolls Royce Plc | Engine nacelle |
US8844553B2 (en) | 2006-10-12 | 2014-09-30 | United Technologies Corporation | Passive boundary layer bleed system for nacelle inlet airflow control |
US8839805B2 (en) | 2006-10-12 | 2014-09-23 | United Technologies Corporation | Passive boundary layer bleed system for nacelle inlet airflow control |
WO2008045051A3 (en) * | 2006-10-12 | 2009-06-18 | United Technologies Corp | Gas turbine nacelle comprising a passive boundary lazer bleed system and method of controlling turbulent airflow |
US9644535B2 (en) | 2006-10-12 | 2017-05-09 | United Technologies Corporation | Passive boundary layer bleed system for nacelle inlet airflow control |
EP1988266B1 (en) * | 2007-04-24 | 2014-11-26 | United Technologies Corporation | Nacelle assembly having inlet airfoil for a gas turbine engine |
RU2490177C2 (en) * | 2011-09-21 | 2013-08-20 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования Иркутский государственный университет путей сообщения (ФГБОУ ВПО ИрГУПС) | Device to prevent ingress of foreign matters into engine |
RU2491208C2 (en) * | 2011-09-21 | 2013-08-27 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования Иркутский государственный университет путей сообщения (ФГБОУ ВПО ИрГУПС) | Device to protect angine against ingress of foreign objects |
RU2491209C2 (en) * | 2011-09-21 | 2013-08-27 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования Иркутский государственный университет путей сообщения (ФГБОУ ВПО ИрГУПС) | Device to protect angine against ingress of foreign objects |
WO2020212226A1 (en) | 2019-04-17 | 2020-10-22 | Safran Aircraft Engines | Turbojet comprising a nacelle with an air intake for promoting a reverse thrust phase |
FR3095241A1 (en) * | 2019-04-17 | 2020-10-23 | Safran Aircraft Engines | Turbojet nacelle air inlet comprising a circulation line to promote a thrust reversal phase |
US11739688B2 (en) | 2019-04-17 | 2023-08-29 | Safran Aircraft Engines | Turbojet comprising a nacelle with an air intake for promoting a reverse thrust phase |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PLNP | Patent lapsed through nonpayment of renewal fees |