专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

21. 发明专利

GB2203105A Wing mounted ducted fan gas turbine powerplant 未知
公开(公告)号：GB2203105A
公开(公告)日：1988-10-12
申请号：GB8801275
申请日：1988-01-21
申请人： ROLLS ROYCE PLC
发明人： MULLINS JOHN ALBERT
IPC分类号： B64C21/04 , B64D27/18 , B64D27/12 , B64C21/00 , F02K1/00
摘要： A ducted fan gas turbine powerplant 10 is located in overlapping relationship with an aircraft wing 12 via a pylon 14. Deflector flaps 22 are provided in the overlapping portion of the powerplant, which are movable soils to cause deflection of fan air which is ejected from the ducted tan, onto the wing upper surface during take off and/or landing of an associated aircraft. The flaps 22 may have trim tabs 26.

22. 发明专利

GB1249123A DUCTED FAN GAS TURBINE ENGINE 未知
公开(公告)号：GB1249123A
公开(公告)日：1971-10-06
申请号：GB3053068
申请日：1968-06-26
申请人： ROLLS ROYCE
发明人： MULLINS JOHN ALBERT , WARD PETER ARTHUR
IPC分类号： F02K1/68
摘要： 1,249,123. Thrust reversers. ROLLSROYCE Ltd. 9 June, 1969 [26 June, 1968], No. 30530/68. Heading B7G. Doors 21 controlling openings 20 in a ducted fan gas turbine engine jet pipe 14 are linked to clam shell doors 17 of a jet pipe thrust reverser or spoiler 16 so as to open into and spoil the discharge from the fan duct 13 when the doors 17 close the pipe 14. The doors 21 do not extend to the lowermost portion of the jet pipe 14 and, when open, their upstream edges 23 are in alignment with the fan duct boundary. The doors 21 are hinged, at the top, to a pylon 12 supporting the engine from an aircraft wing and, at the bottom, to the pipe 14.

23. 发明专利

GB1200879A IMPROVEMENTS RELATING TO THE SILENCING OF GAS TURBINE ENGINES 未知
公开(公告)号：GB1200879A
公开(公告)日：1970-08-05
申请号：GB2889469
申请日：1967-04-05
申请人： ROLLS ROYCE
发明人： MULLINS JOHN ALBERT , MORRIS GEOFFREY WILLIAM , WARD PETER ARTHUR
IPC分类号： F02C7/042 , F02C7/045
摘要： 1,200,879. Gas turbine engines. ROLLS ROYCE Ltd. March 28, 1968 [April 5, 1967], No. 28894/69. Divided out of 1, 190, 774. Heading F1G. A gas turbine jet propulsion engine has an air intake 12 defined by a double walled casing 14 containing circumferentially arranged overlapping sheet members 80 which can be moved axially of the casing 14 to a position, shown dotted, in which the upstream ends 16 of the members 80 effect choking of the intake to prevent or reduce engine noise passing therethrough in an upstream direction. The members 80 run on tracked rollers 18.

24. 发明专利

GB1190774A Improvements relating to the Silencing of Gas Turbine Engines 未知
公开(公告)号：GB1190774A
公开(公告)日：1970-05-06
申请号：GB1560267
申请日：1967-04-05
申请人： ROLLS ROYCE
发明人： WARD PETER ARTHUR , MULLINS JOHN ALBERT , MORRIS GEOFFREY WILLIAM
IPC分类号： F02C7/042 , F02C7/045
摘要： 1,190,774. Gas turbine engines. ROLLSROYCE Ltd. March 28, 1968 [April 5, 1967], No.15602/67. Heading F1G. A gas turbine jet propulsion engine has an air intake passage 24 leading to the engine compressor 12 and angularly spaced flaps 72 pivoted at their downstream ends to the intake casing 20 so as to be movable into a position, shown dotted, in which they effect choking of the passage 24 to prevent or reduce engine noise passing therethrough in an upstream direction. When the flaps 72 are moved to their choking position they uncover ducts 76 in the casing 20 so that some of the incoming air is bled-off to atmosphere through the ducts. The outer ends of the latter have flaps 78 which open and close in unison with flaps 72. 1,190,776. Gas turbine plant: hot gas engines. PHILIPS' GLOEILAMPENFABRIEKEN N. V. May 9, 1967 [May 11, 1966], No.21425/67. Heading F1G and F1S. [Also in Division F4] Means for supplying heat to an apparatus converting the heat into mechanical energy (e. g. a hot-gas engine or a turbo-compressor unit) comprises a first container in which the heat is generated by an exothemic reaction between a liquid metal or metal mixture and a controlled dose of a reacting first medium supplied from a second container through a communicating duct, through which also is supplied to the first container a second medium (e. g. helium or argon) chemically inert to the reaction in the first container, said first container having an outlet for this medium. Fig. 1 shows a hot-gas engine 2-9 the working fluid of which is heated in a heat exchanger 11-13 immersed in the contents of container 15 (the first container) which are agitated by a stirrer 30 or circulated by a pump 32, Fig. 2, (not shown). On starting, electric heaters 21 melt the metal or metal mixture in the container 15. The reacting first medium is in a container 17 (the second container) and the insert second medium is in a container 23 and these media are then allowed to flow together via lines 24, 18 and ports 19 into the container 15 where the reacting medium immediately generates heat whilst the inert medium passes through the container 15 to an outlet duct 26 therefrom, and is returned by a pump 27 to the container 23. Carry-over of particles and metal vapour into the duct 26 is prevented by separating means 28. When the reaction is to be stopped by closure of valve 20 the continuing flow is inert gas from container 23 prevents back-flow of liquid metal into the duct 18 from the container 15. The metal in the container 15 may comprise Li, Na, K, Mg, Al, or one of the rare earth metals or mixtures thereof. The reacting medium in container 17 may be oxygen, a halogen or a halogencontaining compound. Particularly, carbon-fluor compounds can be used. The inert medium may be a gas such a helium or argon. In a modification Fig. 3 (not shown) the hot-gas engine heat exchanger 11-13 may be immersed in a heat-transfer liquid (e. g. NaK) which is circulated through a heat exchanger (43) disposed in a fluid circulation duct 31 in the heat generating container 15. Fig. 4 shows an arrangement whereby power output at shaft 54 is provided by a turbo-compressor unit 50, 53 which includes a heater 51 and a cooler 52. The reacting medium is in a container 58 (controlled by a valve 62) and is admitted to the compressor 53 with the working fluid exhausted from the turbine 50. The reacting medium temperature is said at this stage, to be too low to produce any detrimental reaction within the compressor. From the compressor the reacting medium + working fluid passes via line 55 into chamber 15 wherein heat is generated by the reacting medium, whilst the turbo-compressor working fluid now heated, flows out of container 15 via line 56 to the turbine 50 and thence to point 61 at the inlet side of the compressor where it again is mixed with reacting medium from container 58. 57 shows an alternative position for the container of reacting medium. Carry-over of metal particles or vapour into line 56 from container 15 is prevented by separating means (not shown) e.g. in line 56. In a modification Fig. 5 (not shown) the turbocompressor working fluid is a separate fluid circulated via liner 55, 56 through a heat exchanger (60) immersed in the contents of container 15.

25. 发明专利

GB1106803A Aircraft power plant 未知
公开(公告)号：GB1106803A
公开(公告)日：1968-03-20
申请号：GB3387165
申请日：1965-08-06
申请人： ROLLS ROYCE
发明人： MULLINS JOHN ALBERT
IPC分类号： B64C29/00
摘要： 1,106,803. Aircraft vertical lift engine arrangements. ROLLS-ROYCE Ltd. 29 July, 1966 [6 Aug., 1965], No. 33871/65. Heading B7G. Aircraft vertical lift engines 15 are arranged one behind another within a housing 14, the engines being pivotable from an inoperative position when the engine axis is horizontal to operative positions (e.g. as shown dotted in Fig. 2) the engine thrust being directed mainly vertically with a forward and/or rearward component. In this inoperative position the housing 14 is closed, a smooth outline being formed by the engine portions 25 and spacer portions 26 of the housing. Before turning the engines 15 to an operative position the spacer portions 26 are moved, these may be split into two parts 30, 31, which are separated and slid forward over the engine portions 26 to move with the engines when they are pivoted. There may be two rows of engines side by side, Fig. 1 (not shown). Each engine 15 may comprise an air intake 20, a compressor 21 possibly made largely of plastics, combustion equipment 22, a turbine 23, and a variable area nozzle 24. The main forward propulsion jet engines may be mounted adjacent the tail plane.

26. 发明专利

FR1496176A 未知
公开(公告)号：FR1496176A
公开(公告)日：1967-09-29
申请号：FR72272
申请日：1966-08-05
申请人： ROLLS ROYCE
发明人： MULLINS JOHN ALBERT
IPC分类号： B64C29/00

27. 发明专利

GB1074068A Mounting arrangement for gas turbine jet propulsion engines 未知
公开(公告)号：GB1074068A
公开(公告)日：1967-06-28
申请号：GB5351866
申请日：1964-09-22
申请人： ROLLS ROYCE
发明人： WARD PETER ARTHUR , MULLINS JOHN ALBERT , BRYAN-BROWN MARTIN HUME
IPC分类号： B64C29/00
摘要： 1,074,068. Mounting jet propulsion engines. ROLLS ROYCE Ltd. June 15, 1965 [Sept. 22, 1964], No. 53518/66. Divided out of 1,074,067. Heading B7G. [Also in Division F1] A gas turbine jet propulsion engine has an exhaust gas deflector fixed to the engine and attached to the structure of an aircraft by a mounting that transmits all the engine thrust and some of the weight, the mounting comprising a swinging link (23) pivoted about an axis parallel to the engine axis, which takes all the thrust loads, and a stay or stays (26) which prevent angular movement of the engine about its axis. The two stays (26) described lie at a tangent to the engine casing and depend from a single suspension point attached to the aircraft structure. A second mounting (Fig. 3, not shown) carries the rest of the weight of the engine and comprises two similar stays (30). The engine is mounted parallel to the longitudinal axis of the aircraft in a wing mounted pod and has a forward propulsion nozzle (17) and a deflector (15) for diverting the exhaust through a downwardly directed nozzle (18) of the cascade or elbow-bend type. The deflector is mounted on the engine casing by a sleeve (14) and flange (15), and the first mounting is attached to the sleeve.

28. 发明专利

DE1210329B 未知
公开(公告)号：DE1210329B
公开(公告)日：1966-02-03
申请号：DER0034430
申请日：1963-02-11
申请人： ROLLS ROYCE
发明人： MULLINS JOHN ALBERT , ABBEY DARLEY , MAGUIRE ADDISON CHARLES
IPC分类号： F02K1/00

29. 发明专利

FR1382709A 未知
公开(公告)号：FR1382709A
公开(公告)日：1964-12-18
申请号：FR964037
申请日：1964-02-17
申请人： ROLLS ROYCE
发明人： WILDE GEOFFREY LIGHT , WARD PETER ARTHUR , PETRIE JAMES ALEXANDER , MULLINS JOHN ALBERT , MORTLOCK JAMES
IPC分类号： B64C29/00

30. 发明专利

GB2200878B IMPROVEMENTS IN OR RELATING TO AIRCRAFT AND POWERPLANT COMBINATIONS 未知
公开(公告)号：GB2200878B
公开(公告)日：1990-09-19
申请号：GB8729684
申请日：1987-12-21
申请人： ROLLS ROYCE PLC
发明人： MULLINS JOHN ALBERT
IPC分类号： B64D27/26 , B64C7/00 , B64C7/02 , B64D29/02
摘要： An aircraft has a ducted fan gas turbine engine connected thereto by an underwing mounting arrangement. Links connect the engine to wing main beams and are connected only to that side of the engine which is inboard with respect to the fuselage of the aircraft. An aerodynamically shaped box structure surrounds the links and obviates the gap between engine and wing on the inboard side of the engine.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式