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51. 发明专利

DE1222737B 未知
公开(公告)号：DE1222737B
公开(公告)日：1966-08-11
申请号：DER0035767
申请日：1963-07-26
申请人： ROLLS ROYCE
发明人： BRACEY KENNETH EDWARD , BEALE RICHARD DERBY , WILDE GEOFFREY LIGHT
IPC分类号： F01D17/16

52. 发明专利

FR1453962A 未知
公开(公告)号：FR1453962A
公开(公告)日：1966-07-22
申请号：FR27565
申请日：1965-08-06
申请人： ROLLS ROYCE
发明人： WILDE GEOFFREY LIGHT
IPC分类号： B64C27/18

53. 发明专利

GB1031339A Aircraft lift-producing arrangement 未知
公开(公告)号：GB1031339A
公开(公告)日：1966-06-02
申请号：GB5021264
申请日：1964-12-09
申请人： ROLLS ROYCE
发明人： WILDE GEOFFREY LIGHT , MONAGHAN WILLIAM THOMAS
IPC分类号： B64C23/00
摘要： 1,031,339. Boundary layer control. ROLLSROYCE Ltd. Dec. 9, 1964, No. 50212/64. Heading F2R. [Also in Division B7] An aircraft lift producing arrangement comprises a gas deflector member mounted at the trailing edge of an aircraft wing, a jet engine arranged to direct gases against a first surface and over a second surface of the gas deflector member, being positioned or positionable so that the gases directed against the said first surface are deflected downwardly thereby and so that the gases directed over the said second surface serve to increase the energy of boundary layer flow thereover, and means for directing a flow of gas from the engine over the upper surface of the wing so as to increase the energy of the boundary layer flow thereover. A gas turbine engine 12, Fig. 1, not shown, provided solely for lift, is mounted in a pod 11 beneath a wing 10, the jet pipe 17 being shaped to form a narrow elongated nozzle 22. Exhaust gases pass also through a pipe 26 and over the upper surface of a flap 23 to increase the energy of the boundary layer flow, the flap when deflected as shown reacting with the jet gas to provide lift. Air from the compressor is directed through a pipe 30 over the upper surface of the wing to increase the energy of boundary layer flow or it may be directed to the upper surface of the flap in place of the gas delivered through pipe 26. In a further embodiment, the engine is mounted in the wing and exhaust gases are delivered directly over the upper and lower surfaces of the flap.

54. 发明专利

FR1432346A 未知
公开(公告)号：FR1432346A
公开(公告)日：1966-03-18
申请号：FR16074
申请日：1965-05-06
申请人： ROLLS ROYCE
发明人： WILDE GEOFFREY LIGHT , BILL ARTHUR , COPLIN JOHN FREDERICK
IPC分类号： F23R3/16 , F23R3/28

55. 发明专利

DE1212242B 未知
公开(公告)号：DE1212242B
公开(公告)日：1966-03-10
申请号：DER0023575
申请日：1958-06-27
申请人： ROLLS ROYCE
发明人： WILDE GEOFFREY LIGHT , HOWELL WALTER THOMAS
IPC分类号： F04D21/00 , F04D29/32

56. 发明专利

GB937270A Swivelling nozzles, e.g. for gas turbine engines 未知
公开(公告)号：GB937270A
公开(公告)日：1963-09-18
申请号：GB3046161
申请日：1961-08-23
申请人： ROLLS ROYCE
发明人： WILDE GEOFFREY LIGHT , HOBSON MICHAEL JOHN
IPC分类号： B64C9/38 , B64C29/00
摘要： 937,270. Aircraft jet propulsion plant. ROLLS-ROYCE Ltd. Aug. 16, 1962 [Aug. 23, 1961], No. 30461/61. Class 4. A swivelling jet propulsion nozzle comprises a casing 11 and first nozzle member 12 pivoted together about an axis passing through the centre of curvature of co-operating part spherical surfaces 15, 16 on the casing and member 12, and a second nozzle member 13 pivoted to the first member 12 about an axis passing through the centre of curvature of co-operating part spherical surfaces 16, 17 on the two nozzle members. In the Figure, the two axes are colinear at 18, and the casing 11 is itself pivotable about the same axis. The casing is joined to the outlet 10 of a gas turbine engine or a turbo-fan. The two nozzles members are tiltable in the same sense by linkwork 21, 24, 26 operable by a hydraulic jack 20, and this apparatus may be duplicated on the other side of the nozzle. Specification 888,943 is referred to.

57. 发明专利

FR1326763A 未知
公开(公告)号：FR1326763A
公开(公告)日：1963-05-10
申请号：FR898439
申请日：1962-05-23
申请人： ROLLS ROYCE
发明人： WILDE GEOFFREY LIGHT
IPC分类号： B64C23/00 , B64C29/00

58. 发明专利

GB922645A Jet propulsion engine 未知
公开(公告)号：GB922645A
公开(公告)日：1963-04-03
申请号：GB3987561
申请日：1961-11-07
申请人： ROLLS ROYCE
发明人： WILDE GEOFFREY LIGHT , TORRANCE GEOFFREY PETER
IPC分类号： B64C29/00
摘要： 922,645. Jet deflection on aircraft. ROLLSROYCE Ltd. Nov. 7, 1961, No. 39875/61. Addition to 913,312. Class 4. An aircraft jet propulsion engine has an exhaust duet 9 provided with a nozzle 10 comprising a rotatable frame 16 with a plurality of parallel jet deflector vanes 21, the vanes being disposed substantially in a plane which is inclined to the rotational axis 18 of frame 16. A valve 12 having an axis 13 blocks either the jet pipe or the duet 9. The nozzle 10 is mounted by anti-friction bearing 17 on duct 9 and is rotated by a reversible electric motor 26 and a pinion 27 meshing with teeth 28 on frame 16. A flange 20 of frame 16 carries the vanes 21 and has an annular sealing skirt 23. Two engines 5, 6, Fig. 2, are mounted side by side in a pod 7 suspended by a strut 8 from the aircraft; a single drive may be used for rotating the frames 16 of each engine simultaneously.

59. 发明专利

GB776606A Improvements in or relating to centrifugal compressors 未知
公开(公告)号：GB776606A
公开(公告)日：1957-06-12
申请号：GB1108254
申请日：1954-04-14
申请人： ROLLS ROYCE
发明人： WILDE GEOFFREY LIGHT , SMITH VALENTINE JOHNSTONE , STONE AUBREY
IPC分类号： F04D17/02
摘要： 776,606. Centrifugal compressors. ROLLSROYCE, Ltd. May 6, 1955 [April 14, 1954], No. 11082/54. Class 110 (1). A centrifugal compressor comprises an impeller of the kind in which the hub/tip ratio of diameters of the impeller vanes is 0.50 or less at the impeller eye, the Mach number of the incident stream at the vane tips in the impeller eye is at least 0.85 under maximum rotational speed static conditions at sea level, and the maximum peripheral speed at the impeller outlet tip exceeds 1500 feet per second under the same conditions, and an axial-flow stage immediately at the entry to the impeller vanes, the axial-flow stage comprising a row of rotor blades followed by a row of stator blades. The compressor shown, which forms part of a jetpropulsion gas turbine engine, comprises a double-sided centrifugal impeller 10, preceded on each side by toroidal inlet shoots 13, fixed inlet guide vanes 14, and axial-flow rotor blading 15 and stator blading 16. The leading edges of the centrifugal impeller vanes 11, which are shaped to give the necessary entry angles, may be formed as separate rotating guide vanes. The rotor blades 15, which have a hub/tip ratio of about 0.4 at their inlet edges, may be pivoted, as shown, on a ring 20 splined to the rotor shaft 21. Annular swellings 12a may be provided, each affording a rib 18 and shoulders 17 to locate the roots of the blades 16.

60. 发明专利

GB714157A Improvements relating to aircraft gas turbine power plant installations 未知
公开(公告)号：GB714157A
公开(公告)日：1954-08-25
申请号：GB154851
申请日：1951-01-19
申请人： ROLLS ROYCE
发明人： MURRAY FREDERICK REGINALD , WILDE GEOFFREY LIGHT
IPC分类号： F02C7/04
摘要： 714,157. Gas turbine plant. ROLLS-ROYCE, Ltd. April 18, 1952 [Jan. 19, 1951], No. 1548/51. Class 110(3) [Also in Group XXXIII] In an aircraft gas turbine plant having an axialflow compressor, the air intake passage has a wall in which is formed a circumferentially extending slot through which air can be introduced to increase the kinetic energy of the boundary layer of the air flowing through the passage. This prevents unstable running due to the non-uniformity of air flow into the axial-flow compressor 10 which tends to occur when the aircraft is stationary or flying at low speed. Under these conditions, the pressure in the air intake passage 12 is below atmospheric, the pressure difference opening flap valves 20, which may be spring-loaded, to admit additional air to an annular chamber 17, from which it enters the passage 12 by way of an annular slot 16. Preferably, slot 16 extends substantially wholly around the wall of passage 12, a portion 18 of the wall being turned ouwardly. as shown, to form the slot. Swirl imparting devices, which may be adjustable, may be included in the slot 16 and may be additional to, and upstream of the guide vanes, adjustable or otherwise, which are normally provided at the compressor intake. An air intake slot may be formed in the inner fairing 14. to which the auxiliary air is conveyed from chamber 17 through hollow struts 23. To prevent surging or instability in the compressor at low engine speeds, air may be bled from an intermediate stage or stages of the compressor through bleed valves 21 and conveyed, as through a duct 22. to the chamber 17 and thence into the passage 12 The air bleed may be continued throughout the full range of engine speeds so long as the aircraft is stationary or flying at low speed. Hot air for de-icing may be introduced into the passage 12 through chamber 17 and slot 16 and also through additional inlets which ensure that the hot air mixes well with the main body of air in the passage 12. Specifications 579,657. [Group XXXIII], and 587,126 are referred to.

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