GB800380A - Improvements in or relating to intakes for air inspiring apparatus - Google Patents
Improvements in or relating to intakes for air inspiring apparatusInfo
- Publication number
- GB800380A GB800380A GB1329455A GB1329455A GB800380A GB 800380 A GB800380 A GB 800380A GB 1329455 A GB1329455 A GB 1329455A GB 1329455 A GB1329455 A GB 1329455A GB 800380 A GB800380 A GB 800380A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- expansible
- inner body
- intake
- links
- 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
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
800,380. Axial-flow compressors; gas turbine plant. PLESSEY CO., Ltd. May 4,1956 [May 9, 1955], No. 13294/55. Classes 110(1) and 110(3). An air intake comprises a streamlined inner body provided with member disposed circumferentially about the inner body and expansible for reducing the intake area, the expansible member comprising a number of adjacent long, thin and narrow flexible strips lying on the surface of the inner body with their centre lines in planes containing the axis of the inner body. In the aircraft gas turbine engine shown in Fig. 1, the annular intake d of the compressor a can be constricted by moving an expansible part g from a position in which it follows the outline of an inner wall j to the position shown. The part g comprises flexible metal strips q secured at their forward ends to the inner wall and slidable at their rearward ends h along the inner wall. Fluid is admitted to an hydraulic cylinder m to move a member l from the dotted position, thereby extending the strips q through links k. Preferably a rubber or like cover i is provided. The links may be omitted, the expansion being achieved by moving the free ends of the metal strips in the direction of their fixed ends. In a modification, the members k, l, m are omitted, and the part g is inflated by air or other fluid in accordance with the air speed of the aircraft. The air may be supplied by the compressor. Fig. 3 shows an embodiment in which the expansible part is a metal plate r, the outer portion of which is subdivided by radial cuts into segments q<SP>3</SP> which can be extended into the dotted position by a piston m<SP>1</SP> and links k. A centrifugal pump s driven by the turbine supplies hydraulic fluid at a pressure which varies with the turbine speed and therefore with the air speed of the aircraft by way of a spring- biased flow control valve t<SP>1</SP> and a passage m<SP>2</SP> to the cylinder m. A spill passage m<SP>3</SP> leads back to the pump intake by way of a metering orifice m<SP>4</SP>. An elastic cover similar to the cover i shown in Fig. 1 may be provided.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1329455A GB800380A (en) | 1955-05-09 | 1955-05-09 | Improvements in or relating to intakes for air inspiring apparatus |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1329455A GB800380A (en) | 1955-05-09 | 1955-05-09 | Improvements in or relating to intakes for air inspiring apparatus |
Publications (1)
Publication Number | Publication Date |
---|---|
GB800380A true GB800380A (en) | 1958-08-27 |
Family
ID=10020341
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1329455A Expired GB800380A (en) | 1955-05-09 | 1955-05-09 | Improvements in or relating to intakes for air inspiring apparatus |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB800380A (en) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3053488A (en) * | 1959-05-29 | 1962-09-11 | Martin Marietta Corp | Inflatable streamlined enclosure |
US5230603A (en) * | 1990-08-22 | 1993-07-27 | Rolls Royce Plc | Control of flow instabilities in turbomachines |
EP1992810A2 (en) | 2007-05-18 | 2008-11-19 | United Technologies Corporation | Variable contraction ratio nacelle assembly for a gas turbine engine |
EP1607603A3 (en) * | 2004-06-10 | 2009-08-12 | United Technologies Corporation | Gas turbine engine inlet with noise reduction features |
CN102434285A (en) * | 2011-11-21 | 2012-05-02 | 南京航空航天大学 | Special air bag-based axially-symmetrical deformable air inlet channel |
GB2552503A (en) * | 2016-07-26 | 2018-01-31 | Rolls Royce Plc | Gas turbine engine |
EP3339166A1 (en) * | 2016-12-21 | 2018-06-27 | Airbus Operations, S.L. | Aircraft with a variable fuselage surface for boundary layer optimization |
CN110259580A (en) * | 2019-07-01 | 2019-09-20 | 哈尔滨工业大学 | A kind of DSI air intake duct of deformable adjusting |
GB2580759A (en) * | 2018-12-04 | 2020-07-29 | Borgwarner Inc | Variable inlet diameter unit |
CN112664359A (en) * | 2019-10-16 | 2021-04-16 | 上海汽车集团股份有限公司 | Water spray gasoline engine and control system and control method thereof |
-
1955
- 1955-05-09 GB GB1329455A patent/GB800380A/en not_active Expired
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3053488A (en) * | 1959-05-29 | 1962-09-11 | Martin Marietta Corp | Inflatable streamlined enclosure |
US5230603A (en) * | 1990-08-22 | 1993-07-27 | Rolls Royce Plc | Control of flow instabilities in turbomachines |
US8286654B2 (en) | 2004-06-10 | 2012-10-16 | United Technologies Corporation | Gas turbine engine inlet with noise reduction features |
EP1607603A3 (en) * | 2004-06-10 | 2009-08-12 | United Technologies Corporation | Gas turbine engine inlet with noise reduction features |
US7739865B2 (en) | 2004-06-10 | 2010-06-22 | United Technologies Corporation | Gas turbine engine inlet with noise reduction features |
EP1992810A2 (en) | 2007-05-18 | 2008-11-19 | United Technologies Corporation | Variable contraction ratio nacelle assembly for a gas turbine engine |
EP1992810A3 (en) * | 2007-05-18 | 2013-04-24 | United Technologies Corporation | Variable contraction ratio nacelle assembly for a gas turbine engine |
US8727267B2 (en) | 2007-05-18 | 2014-05-20 | United Technologies Corporation | Variable contraction ratio nacelle assembly for a gas turbine engine |
CN102434285A (en) * | 2011-11-21 | 2012-05-02 | 南京航空航天大学 | Special air bag-based axially-symmetrical deformable air inlet channel |
GB2552503A (en) * | 2016-07-26 | 2018-01-31 | Rolls Royce Plc | Gas turbine engine |
EP3339166A1 (en) * | 2016-12-21 | 2018-06-27 | Airbus Operations, S.L. | Aircraft with a variable fuselage surface for boundary layer optimization |
GB2580759A (en) * | 2018-12-04 | 2020-07-29 | Borgwarner Inc | Variable inlet diameter unit |
CN110259580A (en) * | 2019-07-01 | 2019-09-20 | 哈尔滨工业大学 | A kind of DSI air intake duct of deformable adjusting |
CN112664359A (en) * | 2019-10-16 | 2021-04-16 | 上海汽车集团股份有限公司 | Water spray gasoline engine and control system and control method thereof |
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