公开(公告)号：US08297038B2

公开(公告)日：2012-10-30

申请号：US12877493

申请日：2010-09-08

申请人： Richard G. Stretton

发明人： Richard G. Stretton

IPC分类号： B63H11/00

CPC分类号： F01D25/18 ,  B64D29/04 ,  B64D2027/005 ,  F02C7/14 ,  Y02T50/66 ,  Y02T50/675

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.

摘要翻译： 一种飞行器推进装置，包括具有压缩机的燃气涡轮机飞机发动机，油系统，其构造成将发动机机油引导通过安装到飞行器部件的外表面的热交换器，以便将空气动力学表面的一部分限定为环境空气流 以及将压缩机流体连接到热交换器的管道布置。 一种操作燃气轮机飞机发动机的方法，所述方法包括以下步骤：（a）使发动机机油通过热交换器，从而与环境空气进行热交换; 和（b）引导从压缩机沿着管道装置抽出的压缩机气体的排出流，并与热交换器中的发动机油进行热交换关系，其中选择性地执行引导步骤（b）。

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：US20100284790A1

公开(公告)日：2010-11-11

申请号：US12768316

申请日：2010-04-27

申请人： Clare L. POOL ,  Kenneth F. Udall ,  Richard G. Stretton ,  Julian M. Reed

发明人： Clare L. POOL ,  Kenneth F. Udall ,  Richard G. Stretton ,  Julian M. Reed

IPC分类号： F04D29/66

CPC分类号： F01D21/045 ,  F01D5/16 ,  F01D25/06

摘要： A gas turbine engine fan casing duct wall comprises an intake section and a containment casing, provided respectively with flanges. An acoustic flutter damper is secured between the flanges. The acoustic flutter damper has a skin accommodating an internal structure that dampens fan blade flutter. The skin is secured to the flanges at separate locations. In normal operation of the engine, the internal structure is sufficiently robust to support loads transmitted through the acoustic flutter damper between the intake section and the containment casing. If a blade or blade fragment detaches, the resulting deflection wave in the containment case ruptures the internal structure, and the load path between the intake section and the containment casing passes along the skin, which consequently maintains the connection between the intake duct and the containment casing, while permitting substantial radial deflection of the containment casing relative to the intake section.

摘要翻译： 燃气涡轮发动机风扇壳体管道壁包括分别设置有凸缘的进气部分和容纳壳体。 声波阻尼器固定在凸缘之间。 声波阻尼器具有容纳内部结构的皮肤，其阻尼风扇叶片的颤动。 皮肤在不同的位置固定在法兰上。 在发动机的正常操作中，内部结构足够坚固以支撑通过吸气部分和容纳壳体之间的声波阻尼器传递的载荷。 如果叶片或叶片碎片分离，则容纳壳体中产生的偏转波使内部结构破裂，并且进气部分和收容壳体之间的载荷路径沿着皮肤通过，从而保持进气管道与容纳物之间的连接 同时允许容纳壳体相对于进气部分的大量径向偏转。

公开(公告)号：US20090071122A1

公开(公告)日：2009-03-19

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： F02K3/02

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：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：US08444085B2

公开(公告)日：2013-05-21

申请号：US13232311

申请日：2011-09-14

申请人： Richard G. Stretton ,  Kenneth F. Udall

发明人： Richard G. Stretton ,  Kenneth F. Udall

IPC分类号： B64D27/26

CPC分类号： B64D27/14 ,  B64D27/12 ,  B64D2027/026

摘要： A support structure is provided for attaching a gas turbine engine to a pylon. The gas turbine engine has an engine casing surrounding an engine core, and the pylon has first and second attachment positions, the second attachment position being forward of the first attachment position relative to the working gas flow direction through the engine. The support structure has three elongate members joined to form a triangular frame encircling the engine casing. A first vertex of the triangular frame attaches to the pylon via a first attachment arrangement at the first attachment position. Two thrust struts respectively extend from the other two vertices of the triangular frame and attach to the pylon via a second attachment arrangement at the second attachment position. Three engine connection formations extend from the respective vertices of the triangular frame to positions on the engine casing to connect the support structure to the engine casing.

摘要翻译： 提供了用于将燃气涡轮发动机附接到塔架的支撑结构。 燃气涡轮发动机具有围绕发动机芯的发动机壳体，并且塔架具有第一和第二附接位置，第二安装位置相对于通过发动机的工作气体流动方向在第一附接位置的前方。 支撑结构具有连接的三个细长构件，以形成围绕发动机壳体的三角形框架。 三角形框架的第一顶点经由第一连接装置在第一附接位置附接到塔架。 两个推力支柱分别从三角形框架的其他两个顶点延伸，并通过第二附接装置在第二附接位置附接到塔架。 三个发动机连接结构从三角架的相应顶点延伸到发动机壳体上的位置，以将支撑结构连接到发动机壳体。

公开(公告)号：US20120091265A1

公开(公告)日：2012-04-19

申请号：US13232311

申请日：2011-09-14

申请人： Richard G. STRETTON ,  Kenneth F. UDALL

发明人： Richard G. STRETTON ,  Kenneth F. UDALL

IPC分类号： B64D27/00 ,  B64D27/26

CPC分类号： B64D27/14 ,  B64D27/12 ,  B64D2027/026

摘要： A support structure is provided for attaching a gas turbine engine to a pylon. The gas turbine engine has an engine casing surrounding an engine core, and the pylon has first and second attachment positions, the second attachment position being forward of the first attachment position relative to the working gas flow direction through the engine. The support structure has three elongate members joined to form a triangular frame encircling the engine casing. A first vertex of the triangular frame attaches to the pylon via a first attachment arrangement at the first attachment position. Two thrust struts respectively extend from the other two vertices of the triangular frame and attach to the pylon via a second attachment arrangement at the second attachment position. Three engine connection formations extend from the respective vertices of the triangular frame to positions on the engine casing to connect the support structure to the engine casing.

摘要翻译： 提供了用于将燃气涡轮发动机附接到塔架的支撑结构。 燃气涡轮发动机具有围绕发动机芯的发动机壳体，并且塔架具有第一和第二附接位置，第二安装位置相对于通过发动机的工作气体流动方向在第一附接位置的前方。 支撑结构具有连接的三个细长构件，以形成围绕发动机壳体的三角形框架。 三角形框架的第一顶点经由第一连接装置在第一附接位置附接到塔架。 两个推力支柱分别从三角形框架的其他两个顶点延伸，并通过第二附接装置在第二附接位置附接到塔架。 三个发动机连接结构从三角架的相应顶点延伸到发动机壳体上的位置，以将支撑结构连接到发动机壳体。

公开(公告)号：US20110268563A1

公开(公告)日：2011-11-03

申请号：US13087877

申请日：2011-04-15

申请人： Richard G. STRETTON

发明人： Richard G. STRETTON

IPC分类号： F01D5/08

CPC分类号： F01D25/12 ,  F01D25/18 ,  F02C7/14 ,  F02K3/062 ,  F02K3/072 ,  Y02T50/675

摘要： A heat exchanger arrangement for a gas turbine engine. The arrangement including a flow path within an outer cowl, which flow path locates a heat exchanger part way therealong. A valve is provided at an inlet end of the flow path to selectively receive fluid into the flow path from outside of the cowl and/or from a pressurised fluid flow. An exit from the flow path includes a plenum chamber to receive exhausted coolant flows from the heat exchanger and possibly other exhaust flows. The heat exchanger exhaust flow is then utilised to provide cooling to engine structures.

摘要翻译： 一种用于燃气涡轮发动机的热交换器装置。 该布置包括在外罩内的流动路径，该流动路径沿着其中的一部分方式定位热交换器。 阀设置在流路的入口端，以选择性地将流体从罩的外部和/或加压流体流接收到流路中。 从流动路径的出口包括用于接收来自热交换器和可能的其它排气流的排出的冷却剂流的增压室。 然后利用热交换器废气流向发动机结构提供冷却。

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。