公开(公告)号：US08453458B2

公开(公告)日：2013-06-04

申请号：US12087778

申请日：2007-01-23

申请人： John R Whurr ,  Richard G Stretton ,  David M Beaven ,  Nicholas Howarth

发明人： John R Whurr ,  Richard G Stretton ,  David M Beaven ,  Nicholas Howarth

IPC分类号： F02K1/00 ,  B63H11/10

CPC分类号： F02K3/06 ,  F02K1/08 ,  Y02T50/671

摘要： Variation in the available mixing plane areas in an exhaust arrangement of a gas turbine engine enables alteration and configuration for better thermal cycle performance of that engine. A shaped centre fairing is associated with an exit nozzle and a bypass duct such that channels between the fairing, nozzle exit and duct can be adjusted to change the available areas. Such variation is achieved by relative axial displacement, typically of the exit nozzle using an appropriate mechanism.

摘要翻译： 在燃气涡轮发动机的排气装置中的可用混合平面区域的变化使得能够改变和构造以获得该发动机的更好的热循环性能。 成形中心整流罩与出口喷嘴和旁路管道相关联，使得整流罩，喷嘴出口和管道之间的通道可以被调节以改变可用区域。 这种变化通过相对的轴向位移来实现，通常使用合适的机构来排出出口。

公开(公告)号：US07296414B2

公开(公告)日：2007-11-20

申请号：US10954277

申请日：2004-10-01

申请人： Richard G Stretton ,  Peter K Beardsley ,  David M Beaven

发明人： Richard G Stretton ,  Peter K Beardsley ,  David M Beaven

IPC分类号： B64D27/00 ,  F02K3/02

CPC分类号： B64D27/16 ,  B64D27/26 ,  B64D2033/0286

摘要： A mounting assembly (10) for mounting a gas turbine engine on an aircraft. The assembly (10) comprising four equispaced hydraulic piston and cylinder thrust links (16) connecting between the engine fan case (12) and the air intake (14), which intake (14) is mounted to the airframe.

摘要翻译： 一种用于将燃气涡轮发动机安装在飞机上的安装组件（10）。 组件（10）包括连接在发动机风扇壳体（12）和进气口（14）之间的四个等间距的液压活塞和气缸推力连杆（16），该进气口（14）安装到机身上。

公开(公告)号：US07886520B2

公开(公告)日：2011-02-15

申请号：US11785646

申请日：2007-04-19

申请人： Richard G Stretton ,  Pawel R Zakrzewski

发明人： Richard G Stretton ,  Pawel R Zakrzewski

IPC分类号： F02K99/00 ,  F02K3/02

CPC分类号： F01D17/105 ,  B64D2033/024 ,  F01D17/148 ,  F02C3/13 ,  F02C6/08 ,  F02C7/141 ,  F02C7/18 ,  F02C7/185 ,  Y02T50/675

摘要： Within a turbine engine a heat exchanger may be provided to cool compressor air flows to be utilized for cabin ventilation or other functions. A fluid flow acting as a coolant for the heat exchanger is generally drawn from the by-pass duct of the engine and a dedicated outlet duct is provided such that the exhausted fluid flow from the heat exchanger is delivered along the conduit duct to a low pressure region. In such circumstances, an appropriate pressure differential across the heat exchanger is maintained for operational efficiency when required, whilst the exhausted fluid flow is isolated and does not compromise the usual engine ventilation vent exit area sizing. Over-sized ventilation vents would create an aerodynamic step and therefore drag upon the thrust of the engine. Typically, the outlet end of the outlet duct has a variable geometry to enable adjustment in the pressure differential across the heat exchanger such that an air fan valve used to control flow rate through the heat exchanger may not be required.

摘要翻译： 在涡轮发动机内，可提供热交换器以冷却用于机舱通风或其他功能的压缩机空气流。 作为热交换器的冷却剂的流体流通常从发动机的旁路管道抽出，并且提供专用的出口管道，使得来自热交换器的排出的流体流沿导管管道被输送到低压 地区。 在这种情况下，当需要时，保持热交换器两端的适当的压力差，同时耗尽的流体流动是隔离的，并且不损害通常的发动机通风口排出口尺寸。 超大尺寸的通风口将产生空气动力学步骤，因此拖动发动机的推力。 通常，出口管道的出口端具有可变的几何形状，使得能够调节跨过热交换器的压力差，从而可能不需要用于控制通过热交换器的流速的空气风扇阀。

公开(公告)号：US07341225B2

公开(公告)日：2008-03-11

申请号：US10859308

申请日：2004-06-03

申请人： Richard G Stretton ,  Alastair D Moore

发明人： Richard G Stretton ,  Alastair D Moore

IPC分类号： B64D27/00

CPC分类号： F02K1/44 ,  B64D29/02 ,  F05D2260/96

摘要： An aircraft comprising an aeroengine and a noise reflective surface, the aeroengine capable of generating a hot exhaust jet and noise characterized in that the reflective surface is profiled to reflect noise from the aeroengine into the hot exhaust jet thereby attenuating reflected noise.

摘要翻译： 一种包括航空发动机和噪声反射表面的飞行器，能够产生热排气射流和噪声的航空发动机，其特征在于，所述反射表面被成型以将来自航空发动机的噪声反射到热排气射流中，由此衰减反射的噪声。

公开(公告)号：US06474059B2

公开(公告)日：2002-11-05

申请号：US10140301

申请日：2002-05-08

申请人： Richard G Stretton

发明人： Richard G Stretton

IPC分类号： F01N114

CPC分类号： F02K1/72 ,  F05D2250/34

摘要： A thrust reverser for a gas turbine engine (10) comprises cascade structures (20,22) mounted in an engine cowl (12). The cascades (20,22) comprise a plurality of air deflecting vanes (24) arranged in fixed space relationship. At least one of the cascades (22) translates between a first inoperative position where the cascade (22) is stowed radially inward of the cowl (12) and a second operative position where the cascade (22) is clear of the cowl (12) to expose the air deflecting vanes (24). When the trust reverser is operative blocker doors (26) pivot across an annular duct (13) defined between the core engine (11) and the cowl (12) to deflect the airflow passing therethrough to the exposed cascades (20,22) to produce a braking force.

公开(公告)号：US07313920B2

公开(公告)日：2008-01-01

申请号：US11001122

申请日：2004-12-02

申请人： Richard G Stretton ,  Ewan F Thompson

发明人： Richard G Stretton ,  Ewan F Thompson

IPC分类号： F02C7/20

CPC分类号： B64D27/26

摘要： An aircraft engine mounting assembly comprising a bracket arrangement with two plates located either side of an opening in the structural bypass duct. The bracket arrangement mounts two inclined links which connect to the engine. In normal usage, tension/compression from the links will be passed by the bracket arrangement into the airframe. Upon failure of one of the links the bracket arrangement will engage with the structural bypass duct to transmit engine loads into the airframe via the duct.

摘要翻译： 一种飞机发动机安装组件，包括一个支架装置，其中两个板位于结构旁路管道中的开口的两侧。 支架装置安装两个连接到发动机的倾斜连杆。 在正常使用中，来自连杆的张力/压缩将被支架装置传递到机身中。 当一个连杆失效时，支架装置将与结构旁通管道接合，以将发动机负载通过管道传递到机身中。

公开(公告)号：US06434927B1

公开(公告)日：2002-08-20

申请号：US09506596

申请日：2000-02-18

申请人： Richard G Stretton

发明人： Richard G Stretton

IPC分类号： F02K162

CPC分类号： F02K1/72 ,  F05D2250/34

摘要： A thrust reverser for a gas turbine engine (10) comprises cascade structures (20,22) mounted in an engine cowl (12). The cascades (20,22) comprise a plurality of air deflecting vanes (24) arranged in fixed space relationship. At least one of the cascades (22) translates between a first inoperative position where the cascade (22) is stowed radially inward of the cowl (12) and a second operative position where the cascade (22) is clear of the cowl (12) to expose the air deflecting vanes (24). When the trust reverser is operative blocker doors (26) pivot across an annular duct (13) defined between the core engine (11) and the cowl (12) to deflect the airflow passing therethrough to the exposed cascades (20,22) to produce a braking force.

摘要翻译： 用于燃气涡轮发动机（10）的推力反向器包括安装在发动机整流罩（12）中的级联结构（20,22）。 级联（20,22）包括以固定空间关系布置的多个空气偏转叶片（24）。 级联（22）中的至少一个在级联（22）被放置在整流罩（12）的内侧的第一非工作位置和级联（22）离开整流罩（12）的第二操作位置之间平移， 以暴露空气偏转叶片（24）。 当信任反向器是可操作的阻挡门（26）枢转穿过限定在核心发动机（11）和整流罩（12）之间的环形管道（13），以将通过其的气流偏转到暴露的级联（20,22）以产生 制动力。

公开(公告)号：US07523604B2

公开(公告)日：2009-04-28

申请号：US11363040

申请日：2006-02-28

申请人： Alan R Maguire ,  Kenneth F Udall ,  Richard G Stretton

发明人： Alan R Maguire ,  Kenneth F Udall ,  Richard G Stretton

IPC分类号： F02K1/54

CPC分类号： F02C7/20 ,  F02K1/70 ,  F05D2240/55

摘要： A gas turbine engine comprising a core engine surrounded by a core casing, at least one C-duct having radially inner and outer walls and a thrust reverser unit; the engine is mounted to an aircraft pylon via at least one thrust member attached to the core engine; the thrust reverser unit is mounted within the outer wall of the C-duct; the C-duct is secured to the core casing via a vee-groove attachment comprising vee-groove and vee-blade parts, the attachment is arranged to transfer loads between the thrust reverser unit and the pylon; wherein one cooperating part of the attachment is mounted to a torsion box mounted on the inner wall of the C-duct.

摘要翻译： 一种燃气涡轮发动机，包括由芯壳体围绕的核心发动机，至少一个具有径向内壁和外壁的C形管道和推力反向器单元; 发动机通过至少一个连接到核心发动机的推力构件安装到飞机塔架上; 推力反向器单元安装在C导管的外壁内; C导管通过包括vee-groove和vee-blade部件的vee-groove附件固定到芯壳体，该附件被布置成在推力反向器单元和塔架之间传递载荷; 其中所述附件的一个配合部分安装在安装在所述C导管的内壁上的扭转盒上。

公开(公告)号：US07810312B2

公开(公告)日：2010-10-12

申请号：US11785590

申请日：2007-04-18

申请人： Richard G Stretton ,  Martyn Richards

发明人： Richard G Stretton ,  Martyn Richards

IPC分类号： F02K99/00

CPC分类号： F02C7/141 ,  F02K3/06 ,  F02K3/115 ,  Y02T50/671 ,  Y02T50/675

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.

摘要翻译： 在某些情况下，通过热交换器呈现的流体流的回收可以产生关于推力的阻力和损失的问题。 在燃气涡轮发动机中，使用热交换器来提供其它流量的冷却，例如相对于从发动机的核心取得的压缩空气，并用于机舱通风和除冰功能。 通过在壳体的壁中通过出口管提供出口阀，来自热交换器的排出流体流可以在恢复推力的同时以减小的阻力效应返回至旁通流。 阀可以采取在出口计划之前可移动到旁通流中的挡板的形式，以产生静压力的降低，从而吸引流过热交换器的流体流。

公开(公告)号：US07806363B2

公开(公告)日：2010-10-05

申请号：US11187943

申请日：2005-07-25

申请人： Kenneth F Udall ,  Richard G Stretton

发明人： Kenneth F Udall ,  Richard G Stretton

IPC分类号： B64D27/00

CPC分类号： B64D27/26 ,  B64D27/20 ,  B64D2027/266 ,  F02C7/20 ,  F02C7/32 ,  Y02T50/671

摘要： An engine mounting assembly for an engine, e.g. a gas turbine engine comprises a plurality of carrying arrangements. Each carrying arrangement comprises a rear load absorbing assembly. Each load absorbing assembly provides a rear mounting point for an engine carrier. Each carrying arrangement further comprises first and second stabilising members extending forwardly from the rear mounting point of the rear load absorbing assembly to first and second spaced forward mounting points for an engine carrier.

摘要翻译： 用于发动机的发动机安装组件，例如。 燃气涡轮发动机包括多个承载装置。 每个承载装置包括后负载吸收组件。 每个负载吸收组件为发动机载体提供后部安装点。 每个承载装置还包括从后负载吸收组件的后安装点向前延伸到用于发动机载体的第一和第二间隔开的安装点的第一和第二稳定构件。