专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US3532129A Silencing of gas turbine engines 失效
公开(公告)号：US3532129A
公开(公告)日：1970-10-06
申请号：US3532129D
申请日：1969-02-05
申请人： ROLLS ROYCE
发明人： WARD PETER ARTHUR , MULLINS JOHN ALBERT , MORRIS GEOFFREY WILLIAM
IPC分类号： F02C7/045 , F15D1/00
CPC分类号： F02C7/045 , Y10T137/0536

2. 发明授权

US3532100A Silencing of gas turbine engines 失效
标题翻译：气体涡轮发动机沉降
公开(公告)号：US3532100A
公开(公告)日：1970-10-06
申请号：US3532100D
申请日：1969-02-04
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 , F02K11/00
CPC分类号： F02C7/045 , F02C7/042 , Y10T137/0536

3. 发明授权

US3568446A Ducted fan gas turbine engine 失效
标题翻译：导向风机涡轮发动机
公开(公告)号：US3568446A
公开(公告)日：1971-03-09
申请号：US3568446D
申请日：1969-06-17
申请人： ROLLS ROYCE
发明人： MULLINS JOHN ALBERT , WARD PETER ARTHUR
IPC分类号： F02K1/68 , F02K1/20
CPC分类号： F02K1/68
摘要： A DUCTED FAN GAS TURBINE ENGINE HAVING A JET PIPE, WITHIN WHICH A THRUST REVERSER IS MOUNTED, THE JET PIPE HAVING AT LEAST ONE MOVABLE PORTION WHICH IS MOVABLE BETWEEN A CLOSED POSITION, IN WHICH IT CLOSES AN OPENING IN THE JET PIPE, AND AN OPEN POSITION IN WHICH IT OPENS THE SAID OPENING TO A FLOW OF THE JET GASES FROM THE SAID THRUST REVERSER, THE MOVABLE PORTION, WHEN IN THE OPEN POSITION, EXTENDING INTO THE FLOW PATH OF THE FAN AIR SO AS TO CAUSE REVERSAL OF THE LATTER.

4. 发明专利

DE2338046A1 未知
公开(公告)号：DE2338046A1
公开(公告)日：1974-02-14
申请号：DE2338046
申请日：1973-07-26
申请人： ROLLS ROYCE 1971 LTD
发明人： MULLINS JOHN ALBERT , ALBERT MULLINS JOHN
IPC分类号： F02K3/02 , F02K3/04

5. 发明专利

GB1262419A AIRCRAFT ENGINE MOUNTINGS 未知
公开(公告)号：GB1262419A
公开(公告)日：1972-02-02
申请号：GB3331670
申请日：1970-07-09
申请人： ROLLS ROYCE
发明人： MULLINS JOHN ALBERT
IPC分类号： B64D27/02
摘要： 1,262,419. Aircraft engine mountings. ROLLS-ROYCE Ltd. 9 July, 1970, No. 33316/70. Heading B7G. An aircraft 10 has wing tips 28, 30 and a fuselage 24 all with identical mounting surfaces adapted to receive any one of a plurality of engines 12, 14, 16, 18 such as gas turbine engines each having mounting means 26. Each mounting means 26 comprises a stub wing member having the same chordal profile as the wing tips fixed to the engine at one end and machined flat at the other with spigots or recesses arranged so as to mate with the mounting surfaces on the wing tips and with proud portions 32, 34 on the fuselage. Accessories 36 mounted on the wings and/or fuselage may be driven by the adjacent engine through a drive shaft 38 having a sliding splined connection to the accessory. Oil and fuel drains and similar engine features are duplicated in each engine in order that it may be used either way up so as to be interchangeable between the port and starboard sides of the aircraft.

6. 发明专利

GB1074067A Mounting arrangement for jet propulsion engines 未知
公开(公告)号：GB1074067A
公开(公告)日：1967-06-28
申请号：GB2584064
申请日：1964-06-23
申请人： ROLLS ROYCE
发明人： STEWART ALEXANDER , CRESSWELL ROGER ANTHONY , BRYAN-BROWN MARTIN HUME , WARD PETER ARTHUR , MULLINS JOHN ALBERT
IPC分类号： B64C29/00 , F02C7/20 , F02K1/00
摘要： 1,074,067. Aircraft engine mountings. ROLLS-ROYCE Ltd. June 15, 1965 [June 23, 1964; July 10, 1964; Sept. 22, 1964], Nos. 25840/64, 28725/64 and 38705/64. Heading B7G. [Also in Division F1] A jet propulsion engine has an exhaust gas deflector fixed to the engine (e.g. by a sleeve (27) around the engine casing) and attached to the structure of an aircraft by a mounting that transmits all the engine thrust and some of the load, the remaining portion of the weight being carried by a second mounting comprising a yoke (28, Figs. 2-4, not shown) attached to diametrically opposed points on the engine casing by spigot and socket joints (31) and supported on the aircraft by a ball-and-socket joint (29). There may be two ball-and-socket joints (Figs. 5 and 6, not shown), one at each end of a link (134), one connecting the link to the aircraft structure, and one connecting it to the yoke. A spigot (132) on the yoke then engages the engine casing to prevent the yoke pivoting about the diametrically opposed spigot and socket joints (131). The engine is a gas turbine engine mounted in a pod under an aircraft wing, with its axis parallel to the transverse axis of the aircraft. The deflector comprises a ring (22, Figs. 2-4, not shown) fixed to the sleeve (27) and containing a rotatable cascade (15), and the first mounting comprises a spigot and socket joint (19) and a ball-and-socket joint (20) at opposite ends of a horizontal diameter of the ring (22), the socket being in structural members of the pod.

7. 发明专利

DE1242453B 未知
公开(公告)号：DE1242453B
公开(公告)日：1967-06-15
申请号：DER0036585
申请日：1963-11-15
申请人： ROLLS ROYCE
发明人： ROBINSON NORMAN ROBERT , MULLINS JOHN ALBERT , ABBEY DARLEY , WARD PETER ARTHUR
IPC分类号： F02K1/00

8. 发明专利

FR1465028A 未知
公开(公告)号：FR1465028A
公开(公告)日：1967-01-06
申请号：FR46343
申请日：1966-01-18
申请人： ROLLS ROYCE
发明人： MULLINS JOHN ALBERT
IPC分类号： F02K1/00

9. 发明专利

GB2200878A IMPROVEMENTS IN OR RELATING TO AIRCRAFT AND POWERPLANT COMBINATIONS 未知
公开(公告)号：GB2200878A
公开(公告)日：1988-08-17
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.

10. 发明专利

DE1243024B 未知
公开(公告)号：DE1243024B
公开(公告)日：1967-06-22
申请号：DER0037751
申请日：1964-04-22
申请人： ROLLS ROYCE
发明人： MULLINS JOHN ALBERT
IPC分类号： F02K1/00
摘要： 991,220. Jet pipes and nozzles. ROLLSROYCE Ltd. April 17, 1964 [April 25, 1963], No. 16418/63. Heading F1J. [Also in Divisions B7 and F2] An aircraft has a gas turbine jet engine 12, rotatable jet nozzles 27 each rotatable in bearings in the aircraft structure and connected by a connector 25 (Fig. 2) to a duct 24 arranged to receive gas from the engine. As described, the ducts 24 are fixed to the L.P. compressor outlet 23 of a twin shaft engine. The connector has an abutment 30 and a shoulder 35 and is retained - by a flange 31, 32 fixed to the airframe and 40, 41 fixed to the engine casing. The engine may be removed after unbolting the flanges 31, 32 and withdrawing the connector into the broken line position. In another embodiment (Fig. 3, not shown) the connector is retained in the duct by a clamp ring, its other end having a sealing ring engaging a sleeve fixed to the airframe. The engine jet pipe 20 is connected by bolts or by sealing rings, to a T-shaped conduit 21 leading to rotatable nozzles 22.

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