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1. 发明授权

US3421686A Bearing assembly 失效
标题翻译：轴承总成
公开(公告)号：US3421686A
公开(公告)日：1969-01-14
申请号：US3421686D
申请日：1966-05-31
申请人： ROLLS ROYCE
发明人： COPLIN JOHN FREDERICK , LONGLEY PETER , BLACKHURST ROBERT VAUGHAN
IPC分类号： F01D25/16 , F16C35/067 , F04D25/02
CPC分类号： F01D25/162 , F16C35/067 , F16C2360/23

2. 发明专利

GB2224783A Low windage rotor 未知
公开(公告)号：GB2224783A
公开(公告)日：1990-05-16
申请号：GB8209368
申请日：1982-03-30
申请人： ROLLS ROYCE
发明人： COPLIN JOHN FREDERICK
IPC分类号： F01D5/02 , F01D5/14
摘要： A low windage rotor eg. the turbine rotor of a gas turbine engine, comprises a main rotor (24) and at least one auxiliary rotor (28, 29) having a contoured surface which confronts and is spaced from a surface (30, 31) of the main rotor. The auxiliary rotors are arranged to rotate at approximately half the speed of the main rotor, and the contouring of the surface of the auxiliary rotor (28, 29) is arranged to accommodate rolling vortices between the confronting surfaces which reduce windage drag on the surface of the main rotor (24).

3. 发明专利

GB2224096A Low drag surface 未知
公开(公告)号：GB2224096A
公开(公告)日：1990-04-25
申请号：GB8209329
申请日：1982-03-30
申请人： ROLLS ROYCE
发明人： COPLIN JOHN FREDERICK
IPC分类号： B64C21/04 , B64C23/00
摘要： A low drag surface such as an aerofoil comprises at its upstream edge, an intermittent linear vortex producing means (14, 36) which extends transverse to the flow over the surface and produces a succession of rolling vortices extending transverse to said flow. The vortices move across the surface and reduce drag in the manner of roller bearings. In preferred embodiments the vortex producing means is mechanical, in the form of an oscillating part (14) or fluid dynamic, in the form of a nozzle arrangement (Fig 2, not shown). The part (14) is resiliently mounted at (15) on the main structure and oscillated by a crankshaft (20) acting via a lever (18). The nozzle arrangement uses two superimposed slits extending transversely of the flow, through which fluid is ejected alternately.

4. 发明专利

DE3240461A1 未知
公开(公告)号：DE3240461A1
公开(公告)日：1983-05-11
申请号：DE3240461
申请日：1982-11-02
申请人： ROLLS ROYCE
发明人： COPLIN JOHN FREDERICK
IPC分类号： B22D27/04 , B23P15/00 , F01L3/02

5. 发明专利

GB1253659A IMPROVEMENTS IN OR RELATING TO AIRCRAFT 未知
公开(公告)号：GB1253659A
公开(公告)日：1971-11-17
申请号：GB2298968
申请日：1968-05-15
申请人： ROLLS ROYCE
发明人： COPLIN JOHN FREDERICK
IPC分类号： B64C29/00
摘要： 1,253,659. Cooling duct for gas turbine engine. ROLLS-ROYCE Ltd. 16 June, 1969 [15 May, 1968], No. 22989/68. Heading B7G. [Also in Division F1] Exhaust gases from a gas turbine engine 12 (Fig. 1, not shown) are guided through a conduit 16, Fig. 2, enveloped by a casing 24, to turbine blades 18 situated at the radially outer extremities of blades 20 of a lift fan (22). Casing 24 forms with conduit 16 induction nozzles 28, 30, and air passing through inlet 34 forms a low pressure area adjacent nozzle 28, so that ambient air at atmospheric pressure is induced to flow through apertures 17 in the casing 24 and along the annular space 26 defined thereby to fill the low pressure area, where it is entrained in the airflow through inlet 34, thus providing a constant cooling flow around the conduit 16. Also, the hot gases passing out of fan turbine duct 32 create a low pressure area adjacent nozzle 30, and some of the ambient air is induced to flow through nozzle 30. The sizes of apertures 17 may be varied relative to each other, and baffle-shaped members may be placed in the annular space 26 as an air flow control.

6. 发明专利

GB1210202A GAS TURBINE ENGINE 未知
公开(公告)号：GB1210202A
公开(公告)日：1970-10-28
申请号：GB1197769
申请日：1969-03-06
申请人： ROLLS ROYCE
发明人： COPLIN JOHN FREDERICK
IPC分类号： B60Q1/26 , F02C7/047
摘要： 1,210,202. Gas turbine engines. ROLLSROYCE Ltd. March 6, 1969, No.11977/69. Heading F1G. The invention relates to a gas turbine engine in which means are provided for supplying heated air to a member at the inlet end of the engine to effect anti-icing thereof, the air then passing into the intake of the engine. Vortex means are provided to produce vortex flow in the air stream to ensure mixing thereof with ambient air passing into the intake thereby cooling the air stream before it enters the compressor of the engine. A fairing member or bullet 21 is secured to the compressor rotor 20 by means of an annular wall member 22 and a deflector 24 is secured to the member 21 so as to define a passage therebetween through which air heated by compression in the compressor and supplied through duct 23 is passed, the heated air serving to effect anti-icing of the fairing member. A series of vortex-producing members in the form of bosses 25 are mounted at the downstream end 26 of the member 21 and cause eddying of the anti-icing air stream and so mixing of the air stream with the air flowing into the intake of the compressor so that the anti-icing air is cooled before it flows into the compressor. Some of the cooled air may pass through openings 27 and 30 into the interior of the compressor rotor so as to prevent the compressor being heated by the heated air flow. The compressor blades 17 may be made of synthetic resin material which might be damaged by the anti-icing air if it were directed on to them without first being cooled.

7. 发明专利

GB1048968A Combustion chamber for a gas turbine engine 未知
公开(公告)号：GB1048968A
公开(公告)日：1966-11-23
申请号：GB1940464
申请日：1964-05-08
申请人： ROLLS ROYCE
发明人： WILDE GEOFFREY LIGHT , BILL ARTHUR , COPLIN JOHN FREDERICK
IPC分类号： F23R3/16 , F23R3/28
摘要： 1,048,968. Gas turbine combustion chambers. ROLLS-ROYCE Ltd. April 30, 1965 [May 8, 1964], No. 19404/64. Heading F1L. Gas turbine engine combustion equipment comprises outer and inner casings 11, 16 enclosing an annular flame tube 20 having inlet guide vanes 23 mounted in the upstream end thereof to direct air from the engine compressor towards a combustion zone 24. Each guide vane 23 has an internal radially extending fuel duct 25, Fig. 3 (not shown), adjacent its leading edge supplying fuel through drillings (26) into the air flowing therepast. A strut 30 also having fuel supply drillings 32 is mounted intermediate each pair of adjacent guide vanes 23. The guide vanes and struts extend into a dilution air duct 21. Four part-annular vane members 33 extend between adjacent guide vanes 23 to promote mixing of the fuel/air mixture and prevent breakaway of the airstream from the flame tube walls. Hollow turbine nozzle guide vanes 35 are mounted in the downstream portion of the flame tube and direct dilution air from duct 21 into the combustion gases through apertures 37 in the vane walls. In a modification, Fig. 4 (not shown), vane members 33 are replaced by a single member (41) and annular flame stabilizing gutters (42) are provided in the combustion zone 24.

8. 发明专利

GB1003740A Helicopter rotor 未知
公开(公告)号：GB1003740A
公开(公告)日：1965-09-08
申请号：GB2373664
申请日：1964-06-08
申请人： ROLLS ROYCE
发明人： COPLIN JOHN FREDERICK , TAYLOR PAUL ALFRED , PETRIE JAMES ALEXANDER , BRACEY KENNETH EDWARD GEORGE
IPC分类号： B64C27/18 , F02K3/062 , F02K3/072
摘要： 1,003,740. Gas turbine engines. ROLLSROYCE Ltd. June 8, 1964, No. 23736/64. Headings F1G, FIJ and FIT. [Also in Division B7] The invention relates to a helicopter rotor having a plurality of angularly spaced apart blades each blade having mounted at its tip a gas turbine engine which comprises a first shafting on which is mounted a compressor and a turbine of the engine, and a second shafting on which is mounted a free turbine which is driven by the gases passing through the engine, the gases driving the first and second shaftings in opposite angular directions. The engine shown is a gas turbine ducted fan type jet engine. The engine comprises a first shaft 14 on which are mounted a compressor 15 and a turbine 16. The compressor which comprises axial-flow stages 20 and a centrifugal stage 21 supplies air to the combustion section 22, gases from which act on the turbine 16. The first shaft 14 has secured thereto end members 23 and 30, the forward member 23 being supported in a plain bearing 24 and in a ball thrust bearing 27, while the after member 30 is supported in a plain bearing 32. A duct member 33 is supported within the shaft 14 and fuel is supplied thereto from the duct 35, the fuel discharging from the duct member into the combustion section 22 through an annular member 37 having radial ducts. The gases from the turbine 16 pass through an annular duct and then act on a turbine 44, the turbines 16 and 44 rotating in opposite directions. The turbine 44 is mounted on a shaft 41 which is supported at its upstream end in a plain bearing 32A, disposed adjacent the bearing 32, and at its downstream end in a plain bearing 42. The turbine 44 carries fan blades 45 which draw air from the intake 54 through duct 46 and discharge it through vanes 49 into the duct 50 where it mixes with the turbine exhaust gases and discharges through the outlet nozzle. A lubricating oil reservoir is provided at 51 and oil passes therefrom through duct 52 to the chamber 53, the oil then being supplied by means of pump 55 to the plain bearings 32, 32A and 42 through lines 62, 63 and 64. The oil from the bearings returns by way of lines 66, 67 and 68, through oil cooler 70 and duct 71 back to the reservoir 51. The pump 55 is arranged so that it is immersed when the rotor blade is stationary as well as when it is rotating.

9. 发明专利

FR1408624A 未知
公开(公告)号：FR1408624A
公开(公告)日：1965-08-13
申请号：FR989020
申请日：1964-09-23
申请人： ROLLS ROYCE
发明人： WILDE GEOFFREY LIGHT , COPLIN JOHN FREDERICK
IPC分类号： F02K3/062

10. 发明专利

FR1334156A 未知
公开(公告)号：FR1334156A
公开(公告)日：1963-08-02
申请号：FR910031
申请日：1962-09-21
申请人： ROLLS ROYCE
发明人： OLDFIELD THOMAS ALFRED , COPLIN JOHN FREDERICK
IPC分类号： B64C9/38

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