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1. 发明授权

US3492821A Thrust reversing means for a gas turbine bypass engine 失效
标题翻译：用于燃气轮机旁路发动机的逆转装置
公开(公告)号：US3492821A
公开(公告)日：1970-02-03
申请号：US3492821D
申请日：1968-06-14
申请人： ROLLS ROYCE
发明人： MONAGHAN WILLIAM THOMAS , RODGERS LEONARD JOHN
IPC分类号： F02K1/60 , F02K1/74 , F02K1/20 , B64C15/06
CPC分类号： F02K1/605 , F02K1/74

2. 发明授权

US3630452A Variable-area exhaust nozzles for gas turbine engines 失效
标题翻译：用于气体涡轮发动机的可变区排气喷嘴
公开(公告)号：US3630452A
公开(公告)日：1971-12-28
申请号：US3630452D
申请日：1969-09-11
申请人： ROLLS ROYCE
发明人： MONAGHAN WILLIAM THOMAS
IPC分类号： F02K1/12 , B64C15/06
CPC分类号： F02K1/1207
摘要： In a gas turbine engine, a variable-area exhaust nozzle is provided and consists of a plurality of flaps arranged in sideby-side sealing relationship with each other; each flap is hinged about the circumference of the downstream end of the engine in axially overlapping relationship therewith so as to permit rocking of the flaps such that their ends move about the axis of their respective hinges, cam means being provided to effect such rocking; the flaps are mounted so that their respective surfaces will form substantially continuous inner and outer flow surfaces.

3. 发明专利

GB1090351A Aircraft power plant 未知
公开(公告)号：GB1090351A
公开(公告)日：1967-11-08
申请号：GB779666
申请日：1966-02-22
申请人： ROLLS ROYCE
发明人： MONAGHAN WILLIAM THOMAS , WILDE GEOFFREY LIGHT
IPC分类号： B64C23/00
摘要： 1,090,351. Jet propelled aircraft. ROLLS ROYCE Ltd. Feb. 22, 1966, No. 7796/66. Heading B7G. [Also in Division F2] 'An aircraft power plant supplies pressurized gas to at least one ejector nozzle upstream of a flap so that ambient air is entrained and caused to flow over the flap, the proportions flowing over the upper and lower surfaces being controlled by a valve. As described, a by-pass gas turbine engine is mounted under an aircraft wing, and by-pass air from the engine is conveyed by a duct 20 to ejector nozzles 24, 25 separated by a hollow splitter 21. Ambient air passes to the ejector nozzles through ducts 27, 31 from a duct 32 opening on to the lower surface of the wing 16, and through the interior of the splitter 21 from its ends. The ejectors discharge over the upper and lower surfaces of a hinged flap 11. The duct 32 is closed at the lower surface of the wing by a spring-loaded door 33 which opens automatically when suction is applied by the ejectors. The lower ejector nozzle has a greater flow rate than the upper, but this may be varied by a flap 42. The engine exhaust gases pass through a nozzle 15, and more by-pass air is supplied to flow over the upper surface of the wing.

4. 发明专利

GB1249327A IMPROVEMENTS IN OR RELATING TO VARIABLE AREA EXHAUST NOZZLES 未知
公开(公告)号：GB1249327A
公开(公告)日：1971-10-13
申请号：GB4383068
申请日：1968-09-14
申请人： ROLLS ROYCE
发明人： MONAGHAN WILLIAM THOMAS
IPC分类号： F02K1/12
摘要： 1,249,327. Jet propulsion nozzles. ROLLS-ROYCE Ltd. Sept.18, 1969 [Sept.14, 1968], No.43830/68. Heading F1J. A variable area jet propulsion nozzle comprises a plurality of flaps arranged in side-by-side sealing relation with each other and adapted to be hinged to fixed structure in axially overlapping relation therewith so as to permit rocking of the flaps such that the axially opposite ends of each flap move about the axis of the respective hinge, there being means for causing such rocking movement. The assembly shown comprises a jet pipe20 which is disposed within an outer pod 12. The downstream ends of the jet pipe and of the pod lie in the same transverse plane A. A series of flap members 22 are pivotally mounted at pivot points 26 at the downstream end of the jet pipe, the pivot points being substantially at the mid points of the flaps. A cylindrical member 22 is mounted for axial movement on rollers 34 and carries triangular cams 30 which engage against rollers 38 carried by the upstream ends of the flaps 22. The member 32 and cams are moved axially by means of actuators 36 so that the flaps may be moved between the minimum area position shown in full lines and the maximum area position shown in broken lines, the flaps moving to the latter position by pressure of gases within the nozzles as the cams 30 are moved in an upstream direction. The flaps 22 are in sealing engagement with adjacent flaps.

5. 发明专利

GB2121115A Aerofoil vane assembly 未知
公开(公告)号：GB2121115A
公开(公告)日：1983-12-14
申请号：GB8216223
申请日：1982-06-03
申请人： ROLLS ROYCE
发明人： MONAGHAN WILLIAM THOMAS
IPC分类号： F01D9/04 , F01D9/02
摘要： The assembly consists of radially inner and outer members 23 and 24 having tensioned radially extending spokes 25 therebetween; the aerofoil vanes each being formed in two parts 26 and 27 (Fig. 5 not shown) each pair of which are located and secured about pairs of spokes 25.

6. 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.

7. 发明专利

GB978044A Gas turbine engine 未知
公开(公告)号：GB978044A
公开(公告)日：1964-12-16
申请号：GB4250363
申请日：1963-10-28
申请人： ROLLS ROYCE
发明人： MONAGHAN WILLIAM THOMAS
IPC分类号： B64C9/38 , B64C29/00 , F02K1/00
摘要： 978,044. Aircraft propulsion plant. ROLLSROYCE Ltd. Oct. 28, 1963, No. 42503/63. Heading B7G. A gas-turbine engine comprises an annular air duet surrounding an annular gas duct containing a compressor, combustion equipment, and a turbine, so that air is discharged as an annulus surrounding the turbine exhaust gases, a plurality of exhaust gas deflectors each linked to one of a plurality of air deflectors pivotally mounted at the downstream end of the gas duct, and power means directly connected to the air deflectors. The air duct 23 may be a bypass or ram air duct, or, as shown, may contain fan blades 24 integral with the blades of a high-pressure turbine 15 driving a highpressure compressor, a low-pressure turbine 16 driving a low-pressure compressor. Eyelids 32 pivoted at 33 can deflect the turbine exhaust gases, and are joined by links 34 to eyelids 25 pivoted at 26 for deflecting the annular air stream, so that a pneumatic or hydraulic jack 31 operates eyelids 32 and 25 together. The engine may be mounted horizontally, deflection providing lift.

8. 发明专利

GB1130268A Improvements in or relating to gas turbine by-pass engines 未知
公开(公告)号：GB1130268A
公开(公告)日：1968-10-16
申请号：GB3045867
申请日：1967-07-01
申请人： ROLLS ROYCE
发明人： MONAGHAN WILLIAM THOMAS , RODGERS LEONARD JOHN
IPC分类号： F02K1/60 , F02K1/74
摘要： 1,130,268. Deflecting propulsive jets. ROLLSROYCE Ltd. 1 July, 1967, No. 30458/67. Heading B7G. A by-pass jet propulsion engine 20 has its outer casing split on an inclined annular face 40 so that the rear portion 18 may be moved bodily aft by a plurality of jacks 46 together with an aft portion of jet pipe 28, attached to portion 18 by struts 26. The portion 28 is spaced from the forward part of the jet pipe and the gap is filled by a pair of opposed scoop members 34, 36 pivotally mounted on a common axis 38 and each connected by a link 60 to the casing portion 18, aft movement of which causes members 34, 36 to pivot from the full line positions in Fig. 2 to the dotted line positions whereby they block off the by-pass duct 24 and the jet pipe to cause jet gas and by-pass air to flow outwardly and forwardly through the gap in the casing formed by aft movement of portion 18. To increase the effectiveness of the blocking members and as shown more clearly in Fig. 3, each is formed with wings 66, 68 respectively. The opening in the casing may be provided with retractable deflector vanes.

9. 发明专利

GB1119608A Jet pipe with variable effective flow cross-sectional area for a gas turbine engine 未知
公开(公告)号：GB1119608A
公开(公告)日：1968-07-10
申请号：GB4830066
申请日：1966-10-27
申请人： ROLLS ROYCE
发明人： MONAGHAN WILLIAM THOMAS , BROWN MARTIN BRYAN , BARKER CHARLES
IPC分类号： F02K1/09 , F02K1/42
摘要： 1,119,608. Deflecting propulsive jets. ROLLSROYCE Ltd. 27 Oct., 1966, No. 48300/66. Heading B7G. [Also in Division F1] A sleeve valve 25, Fig. 5, disposed around a gas turbine engine jet pipe is axially movable to a position in which circumferentially spaced ports 31 are aligned with circumferentially spaced apertures 18 in the wall 21 of the jet pipe. Exhaust gases then pass through the apertures 18, ports 31 and circumferentially spaced apertures 30 in the engine casing 16 to discharge to atmosphere in a radial direction to provide a thrust-spoiling effect.

10. 发明专利

DE1236343B 未知
公开(公告)号：DE1236343B
公开(公告)日：1967-03-09
申请号：DER0037245
申请日：1964-02-18
申请人： ROLLS ROYCE
发明人： MORTLOCK JAMES , MONAGHAN WILLIAM THOMAS , BEALE RICHARD DERBY , PETRIE JAMES ALEXANDER
IPC分类号： B64C29/00 , B64D27/02 , F02K1/00
摘要： 958,194. Junction pieces. ROLLS-ROYCE Ltd. March 5, 1963, No. 8827/63. Heading F2G. [Also in Divisions B7 and F1] A fluid flow apparatus comprises a cylinder which is provided with an internal axiallyextending helical wall which divides the cylinder into two non-communicating helical compartments, two spaced-apart outlet pipes which respectively communicate with different compartments, and two spaced-apart inlet pipes which are disposed inwardly of the outlet pipes and which respectively communicate with the different compartments, the arrangement being such that fluid flowing through each inlet pipe passes to that outlet pipe which is disposed on the further side of the other inlet pipe. The invention is described with reference to an aircraft having a power plant comprising two gas turbine jet engines 12, 13 disposed side by side on either side of the longitudinal axis of the aircraft. Each engine comprises air compressor means 16, combustion equipment 17 and turbine means 18, also a jet pipe 20, 21. The jet pipes communicate with the inlets 22, 23, of the fluid flow apparatus 24 shown in Fig. 2 which comprises a cylinder 25 disposed transversely of the aircraft, the interior of the cylinder being divided into two compartments 27, 28 by the helical wall 26, the inlet 22 communicating with the compartment 27 and inlet 23 with compartment 28. The engine exhaust gases flow through the chambers as indicated by the arrows 32, 33 and discharge through outlets 30, 31, the gases from either engine discharging through the outlet disposed at the far side of the other engine. The outlets 30, 31 terminate in propulsion nozzles 35. Each engine is also provided with a duct 36 which terminates in a propulsion nozzle 37 whereby a portion of the air compressed in the compressor means 16 may be utilized to provide jet thrust. Combustion equipment may be provided in the ducts 36. Each of the nozzles 35, 37 may be provided with deflector means as disclosed in Specification 813,312 whereby the jet gases may be directed rearwardly, forwardly or downwardly as desired. The inlets 22, 23 of the apparatus 24 are spaced apart by a distance equal to a quarter of the pitch of the helical vane 26, and the outlets 30, 31 by a distance equal to a half of the pitch.

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