GB820366A - Improvements in or relating to retractable guards for air intakes - Google Patents
Improvements in or relating to retractable guards for air intakesInfo
- Publication number
- GB820366A GB820366A GB60156A GB60156A GB820366A GB 820366 A GB820366 A GB 820366A GB 60156 A GB60156 A GB 60156A GB 60156 A GB60156 A GB 60156A GB 820366 A GB820366 A GB 820366A
- Authority
- GB
- United Kingdom
- Prior art keywords
- guard
- portions
- duct
- bars
- wall
- 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
- 239000012530 fluid Substances 0.000 abstract 2
- 230000004048 modification Effects 0.000 abstract 1
- 238000012986 modification Methods 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- 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
- F02C7/055—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with intake grids, screens or guards
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/022—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising bird or foreign object protections
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
820,366. Gas turbine plant. ROLLS-ROYCE Ltd. Jan. 4, 1957 [Jan. 6, 1956], No. 601/56. Class 110(3). A retractable guard for an air intake duct of non-annular form comprises two guard portions each of which is located wholly within the duct and is mounted to pivot about an axis extending across the duct, between an operative position in which the guard portions together extend across the fluid passage, one edge of each guard portion co-operating with a corresponding edge of the other guard portion and another edge of each guard portion co-operating with a wall of the duct and an inoperative position in which the guard portions are substantially out of the path of the fluid flowing through the duct, the guard portions being shaped to conform with the wall of the duct against which they lie in the retracted position. The air intake duct 13 of a gas turbine engine nacelle leads to the entry of an axial-flow engine compressor 16. A pair of guard grid portions 17, mounted to pivot about an axis 25, each comprise a number of rectangular bars arranged in two sets 18, 19. The bars 18 of one set lie in parallel planes and, in the position shown, extend parallel to the axis of the duct 13. The bars 19 of the other set are in planes at right-angles to the planes in which the bars 18 lie. In the operative position, the bars 19 also lie in planes parallel to the axis of the duct 13. The bars 18, 19 may be interconnected by a halving joint. The edges of the guard grid portions are strengthened by parts 21, 22 provided with sockets 26 which engage spigots 27 carried by the nacelle wall 11. A recess 23 is provided in the wall 11 to receive debris collected on the grids when they are moved to the inoperative position. The part 21 co-operates closely with the edge 24 of the recess 23 to prevent this debris becoming loose in flight and entering the intake of the compressor. The part 22 co-operates with the partspherical surface 34 during movement of the guard portions 17 for the same purpose. The portions 17 may be operated by pneumatically or hydraulically-operated rams. A separate ram may be provided for each portion in which case appropriate stops will be necessary. As shown, the portions 17 are interconnected by a pair of links 31 provided with a roller 32 engaging a track 33 and operated by a single ram 28. In addition to the guard grid portions 17, there may be provided a pair of imperforate panels 35, Fig. 3. The rear part 36 of each panel is of part-spherical form and lies outside of the part 34 of the inner wall 11. The panels 35, which contain the recess 23, are pivoted on the spigots 27 and held in the inoperative position by latch mechanism 37. It may be arranged that the aerodynamic forces on the panels 35 are such that on release of the mechanism 37 the panels move to their operative position over the guard grid portions and abut one another on a horizontal plane. In a modification, the guard portions may be made imperforate so that when in the operative position they prevent the flow of air into the engine and so stop it windmilling.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB60156A GB820366A (en) | 1956-01-06 | 1956-01-06 | Improvements in or relating to retractable guards for air intakes |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB60156A GB820366A (en) | 1956-01-06 | 1956-01-06 | Improvements in or relating to retractable guards for air intakes |
Publications (1)
Publication Number | Publication Date |
---|---|
GB820366A true GB820366A (en) | 1959-09-16 |
Family
ID=9707250
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB60156A Expired GB820366A (en) | 1956-01-06 | 1956-01-06 | Improvements in or relating to retractable guards for air intakes |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB820366A (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3253404A (en) * | 1961-06-02 | 1966-05-31 | Hamburger Flugzeugbau Gmbh | Apparatus for and method of prevention of ice formation on aircraft engine air inletorifices |
FR2525278A1 (en) * | 1982-04-19 | 1983-10-21 | Innerspace Corp | TURBOMACHINE AND ESPECIALLY SELF-RELEASING SCREEN |
GB2169661A (en) * | 1984-12-12 | 1986-07-16 | Parmatic Filter Corp | Mounting structural frame for a particle/moisture separator for an air inlet of a gas turbine engine |
US5123242A (en) * | 1990-07-30 | 1992-06-23 | General Electric Company | Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine |
GB2259114A (en) * | 1991-08-28 | 1993-03-03 | Gen Electric | Aircraft engine nacelle profile |
FR2952401A1 (en) * | 2009-11-12 | 2011-05-13 | Eurocopter France | AIR INTAKE OF AN AIRCRAFT TURBOMOTOR, AIRCRAFT PROVIDED WITH SUCH AIR INTAKE AND METHOD FOR OPTIMIZING THE OPERATION OF A TURBOMOTEUR OF AN AIRCRAFT USING AN AIR INTAKE |
CN108291486A (en) * | 2015-11-27 | 2018-07-17 | 赛峰航空器发动机 | It include the turbine of the collector of the foreign matter for recycling in the gas flow |
EP3351752A1 (en) * | 2017-01-24 | 2018-07-25 | Rolls-Royce plc | Gas turbine engine arrangement |
-
1956
- 1956-01-06 GB GB60156A patent/GB820366A/en not_active Expired
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3253404A (en) * | 1961-06-02 | 1966-05-31 | Hamburger Flugzeugbau Gmbh | Apparatus for and method of prevention of ice formation on aircraft engine air inletorifices |
FR2525278A1 (en) * | 1982-04-19 | 1983-10-21 | Innerspace Corp | TURBOMACHINE AND ESPECIALLY SELF-RELEASING SCREEN |
GB2169661A (en) * | 1984-12-12 | 1986-07-16 | Parmatic Filter Corp | Mounting structural frame for a particle/moisture separator for an air inlet of a gas turbine engine |
US5123242A (en) * | 1990-07-30 | 1992-06-23 | General Electric Company | Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine |
GB2259114A (en) * | 1991-08-28 | 1993-03-03 | Gen Electric | Aircraft engine nacelle profile |
FR2952401A1 (en) * | 2009-11-12 | 2011-05-13 | Eurocopter France | AIR INTAKE OF AN AIRCRAFT TURBOMOTOR, AIRCRAFT PROVIDED WITH SUCH AIR INTAKE AND METHOD FOR OPTIMIZING THE OPERATION OF A TURBOMOTEUR OF AN AIRCRAFT USING AN AIR INTAKE |
EP2322782A1 (en) * | 2009-11-12 | 2011-05-18 | Eurocopter | Air intake of a turbine aircraft engine, aircraft equipped with such air intake and method for optimizing the operation of a turbine aircraft engine with an air intake |
RU2471679C2 (en) * | 2009-11-12 | 2013-01-10 | Еврокоптер | Air inlet for turbomotor, aircraft with such air inlet, and method for optimising aircraft turbomotor operation using air inlet |
US8439297B2 (en) | 2009-11-12 | 2013-05-14 | Eurocopter | Air inlet for an aircraft turbine engine, an aircraft provided with such an air inlet, and a method of optimizing the operation of an aircraft turbine engine with the help of an air inlet |
CN108291486A (en) * | 2015-11-27 | 2018-07-17 | 赛峰航空器发动机 | It include the turbine of the collector of the foreign matter for recycling in the gas flow |
EP3351752A1 (en) * | 2017-01-24 | 2018-07-25 | Rolls-Royce plc | Gas turbine engine arrangement |
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