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1. 发明专利

JP2011231767A Gas turbine engine 有权
标题翻译：气体涡轮发动机
公开(公告)号：JP2011231767A
公开(公告)日：2011-11-17
申请号：JP2011101128
申请日：2011-04-28
申请人： Rolls Royce Plc , ロールス‐ロイス、パブリック、リミテッド、カンパニーRolls−Royce Public Limited Company
发明人： STRETTON RICHARD GEOFFREY
IPC分类号： F02C7/042 , F02C7/06 , F02C7/18 , F02K3/062
CPC分类号： F01D25/12 , F01D25/18 , F02C7/14 , F02K3/062 , F02K3/072 , Y02T50/675
摘要： PROBLEM TO BE SOLVED: To provide a heat exchanger arrangement for a gas turbine engine.SOLUTION: The heat exchanger arrangement includes a flow path 31 within an outer cowl 32. The flow path 31 locates a heat exchanger 43 part way therealong. A valve 38 is provided at an inlet end of the flow path 31 to selectively receive fluid into the flow path 31 from the outside of the cowl 32 and/or from a pressurised fluid flow 36. An exit 34 from the flow path 31 includes a plenum chamber to receive exhausted coolant flows from the heat exchanger 43 and possibly other exhaust flows. The heat exchanger exhaust flow 34 is then utilized to provide cooling to engine structures.
摘要翻译：要解决的问题：提供一种用于燃气涡轮发动机的热交换器装置。解决方案：热交换器装置包括在外罩32内的流路31.流动路径31在其一部分方向上定位热交换器43。阀38设置在流路31的入口端处，以从外罩32和/或加压流体流36的外部选择性地将流体接收到流路31中。来自流动路径31的出口34包括以便从热交换器43和可能的其他排气流中接收排出的冷却剂。然后利用热交换器废气流34向发动机结构提供冷却。版权所有（C）2012，JPO＆INPIT

2. 发明专利

DE602005026613D1 Aufhängevorrichtung eines Triebwerks 未知
公开(公告)号：DE602005026613D1
公开(公告)日：2011-04-14
申请号：DE602005026613
申请日：2005-07-22
申请人： ROLLS ROYCE PLC
发明人： UDALL KENNETH FRANKLIN , STRETTON RICHARD GEOFFREY
IPC分类号： B64D27/26 , B64D27/20

3. 发明专利

GB2437377B A gas turbine engine heat exchanger arrangement 未知
公开(公告)号：GB2437377B
公开(公告)日：2008-12-03
申请号：GB0705340
申请日：2007-03-21
申请人： ROLLS ROYCE PLC
发明人： RICHARDS MARTYN , STRETTON RICHARD GEOFFREY
IPC分类号： F02C3/04 , F02C7/14 , F02K3/02 , F02K3/06 , F02K3/115
摘要： In certain circumstances recovery of a fluid flow presented through a heat exchanger into another flow can create problems with respect to drag and loss of thrust. In gas turbine engines heat exchangers are utilized for providing cooling of other flows such as in relation to compressor air taken from the core of the engine and utilized for cabin ventilation and de-icing functions. By providing an outlet valve through an outlet duct in a wall of a housing the exhaust fluid flow from the heat exchanger can be returned to the by-pass flow with reduced drag effects whilst recovering thrust. The valve may take the form of a flap displaceable into the by-pass flow before an exit plan to create a reduction in static pressure drawing fluid flow through the heat exchanger.

4. 发明专利

GB2437295B Aeroengine ventilation system 未知
公开(公告)号：GB2437295B
公开(公告)日：2008-06-25
申请号：GB0607794
申请日：2006-04-20
申请人： ROLLS ROYCE PLC
发明人： STRETTON RICHARD GEOFFREY
IPC分类号： F02C7/14 , F02C7/18 , F02K1/06 , F02K1/08 , F02K1/12

5. 发明专利

DE602004012272T2 未知
公开(公告)号：DE602004012272T2
公开(公告)日：2008-06-05
申请号：DE602004012272
申请日：2004-06-30
申请人： ROLLS ROYCE PLC
发明人： STRETTON RICHARD GEOFFREY
IPC分类号： F02C7/32 , F02K3/04
摘要： In order to avoid external bulging (5) to accommodate accessory mechanisms (27) and gearboxes (30) to drive these mechanisms (27) in accordance with the present invention splitter fairings (26) are located within a bypass duct (23) of an engine (20). The bypass duct (23) is defined between a casing (21) and compressor/turbine propulsion core (22). The fairings (26) are of sufficient dimensions to accommodate the accessory mechanisms (27) whilst the bypass duct (23) is appropriately shaped axi-symmetrically to eliminate and balance any blocking effect of these fairings (26) within the duct (23) upon air flow (24). Further fairings (26') may be provided to accommodate oil tank reservoirs (34) as well as filter/heat exchanger mechanisms (35) for the engine (20). In such circumstances, a notional elongate cylindrical profile for the engine (20) is maintained such that a reduced cross section is require for that engine (20) and so allowing a smaller airframe with better sonic boom signature.

6. 发明专利

DE602004012272D1 未知
公开(公告)号：DE602004012272D1
公开(公告)日：2008-04-17
申请号：DE602004012272
申请日：2004-06-30
申请人： ROLLS ROYCE PLC
发明人： STRETTON RICHARD GEOFFREY
IPC分类号： F02C7/32 , F02K3/04
摘要： In order to avoid external bulging (5) to accommodate accessory mechanisms (27) and gearboxes (30) to drive these mechanisms (27) in accordance with the present invention splitter fairings (26) are located within a bypass duct (23) of an engine (20). The bypass duct (23) is defined between a casing (21) and compressor/turbine propulsion core (22). The fairings (26) are of sufficient dimensions to accommodate the accessory mechanisms (27) whilst the bypass duct (23) is appropriately shaped axi-symmetrically to eliminate and balance any blocking effect of these fairings (26) within the duct (23) upon air flow (24). Further fairings (26') may be provided to accommodate oil tank reservoirs (34) as well as filter/heat exchanger mechanisms (35) for the engine (20). In such circumstances, a notional elongate cylindrical profile for the engine (20) is maintained such that a reduced cross section is require for that engine (20) and so allowing a smaller airframe with better sonic boom signature.

7. 发明专利

GB2385382B A cowl structure for a gas turbine engine 未知
公开(公告)号：GB2385382B
公开(公告)日：2006-02-15
申请号：GB0203447
申请日：2002-02-13
申请人： ROLLS ROYCE PLC
发明人： STRETTON RICHARD GEOFFREY , UDALL KENNETH FRANKLIN
IPC分类号： F02C7/04 , B64D29/00 , F01D11/00 , F02C7/045 , F02K1/80 , F02K3/00 , F04D29/16 , F04D29/54 , F04D29/68
摘要： A cowl structure ( 18 ) for a gas turbine engine ( 10 ) comprises an outer skin ( 26 ) defining a first path for a load applied to the engine ( 10 ). The cowl structure ( 18 ) includes an inner skin ( 24 ) defining a second path for the load. The inner and outer skins ( 24, 26 ) are constructed such that a major proportion of the load is transmitted along the first path.

8. 发明专利

GB2473651B Gas turbine aircraft engines and operation thereof 未知
公开(公告)号：GB2473651B
公开(公告)日：2011-08-31
申请号：GB0916491
申请日：2009-09-21
申请人： ROLLS ROYCE PLC
发明人： STRETTON RICHARD GEOFFREY
IPC分类号： F02C7/141 , F02C7/18
摘要： An aircraft propulsion arrangement including a gas turbine aircraft engine having a compressor, an oil system configured to route engine oil through a heat exchanger mounted to an external surface of an aircraft component so as to define part of an aerodynamic surface to a flow of ambient air, and a duct arrangement fluidly connecting the compressor to the heat exchanger. A method of operating the gas turbine aircraft engine, the method involving the steps of: (a) flowing engine oil through the heat exchanger and thus into heat-exchange relationship with the ambient air; and (b) directing a bleed flow of compressor gas drawn from the compressor along the duct arrangement and into heat-exchange relationship with the engine oil in the heat exchanger, wherein the directing step (b) is performed selectively.

9. 发明专利

HK1117214A1 AN ENGINE CORE STAND ARRANGEMENT AND METHOD OF REMOVAL AND TRANSPORTATION OF AN ENGINE CORE 未知
公开(公告)号：HK1117214A1
公开(公告)日：2009-01-09
申请号：HK08107628
申请日：2008-07-10
申请人： ROLLS ROYCE PLC
发明人： STRETTON RICHARD GEOFFREY
IPC分类号： F01D20060101 , F02C20060101 , F02K20060101
摘要： Transportation of larger diameter gas turbine engines can be problematic. In such circumstances it is known to separate the fan assembly (30) from the engine core (1) and other parts to facilitate transportation. Separation of the fan assembly (30) and engine core (1) can require a gantry which adds to inconvenience and costs. By utilising a platform (2, 44) with suspender members (43) in the form of boot straps (43) which extend down from an existing pylon (31) it is possible to remove an engine core (1) through a carriage dolly (3, 45) which moves along a rail (21 within the platform (2, 44) generally laterally until it is possible to lower the engine upon the platform to ground level. The platform (2, 44) and carriage dolly (3, 45) can then act as a stand for transportation of the engine core.

10. 发明专利

DE602004000737D1 未知
公开(公告)号：DE602004000737D1
公开(公告)日：2006-06-01
申请号：DE602004000737
申请日：2004-06-03
申请人： ROLLS ROYCE PLC
发明人： STRETTON RICHARD GEOFFREY , MOORE ALASTAIR DAVID
IPC分类号： B64D33/04 , B64D29/02 , F02K1/44
摘要： An aircraft comprising an aeroengine (10) and a noise reflective surface (33), the aeroengine (10) capable of generating a hot exhaust jet (30) and noise characterised in that the reflective surface (33) is profiled to reflect noise from the aeroengine (10) into the hot exhaust jet (30) thereby attenuating reflected noise.

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