公开(公告)号：US20110067412A1

公开(公告)日：2011-03-24

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： F02C6/08 ,  F02C7/20 ,  F23R3/26

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

摘要： There is disclosed 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 so as to define part of an aerodynamic surface to the flow of ambient air, and a duct arrangement fluidly connecting the compressor to the heat exchanger. There is also proposed a method of operating the engine, the method involving the steps of: (a) flowing engine oil through the heat exchanger and thus into heat-exchange relationship with said ambient air; and (b) directing a bleed flow of compressor gas drawn from the compressor along said duct arrangement and into heat-exchange relationship with said oil in said heat exchanger, wherein said directing step (h) is performed selectively.

摘要翻译： 公开了一种飞行器推进装置，其包括具有压缩机的燃气涡轮机飞机发动机，油系统构造成将发动机机油引导通过安装的热交换器，以将空气动力学表面的一部分限定为环境空气的流动，以及管道装置 将压缩机流体连接到热交换器。 还提出了一种操作发动机的方法，该方法包括以下步骤：（a）使发动机机油通过热交换器，从而与所述环境空气进行热交换; 和（b）引导从压缩机沿着所述管道装置抽出的压缩机气体的排出流，并与所述热交换器中的所述油进行热交换关系，其中所述引导步骤（h）是选择性地进行的。

公开(公告)号：US20090158704A1

公开(公告)日：2009-06-25

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： F02K1/46 ,  F02K3/02

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：US07484354B2

公开(公告)日：2009-02-03

申请号：US11298599

申请日：2005-12-12

申请人： Richard G Stretton

发明人： Richard G Stretton

IPC分类号： F02C7/32

CPC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.

摘要翻译： 为了避免根据本发明的外部凸起（5）容纳附件机构（27）和齿轮箱（30）以驱动这些机构（27），分流器整流罩26位于 发动机（20）。 旁通管道（23）被限定在壳体（21）和压缩机/涡轮机推进器芯（22）之间。 整流罩（26）具有足够的尺寸以容纳附件机构（27），同时旁路管道（23）被适当地对称地成形，以消除和平衡这些整流罩（26）在管道（23）内的阻塞效应 空气流（24）。 可以提供另外的整流罩（26'）以容纳油箱储存器（34）以及用于发动机（20）的过滤器/热交换器机构（35）。 在这种情况下，保持用于发动机（20）的概念细长的圆柱形轮廓，使得对于该发动机（20）需要减小的横截面，并且因此允许具有更好的声波起点特征的较小的机身。

公开(公告)号：US20080011932A1

公开(公告)日：2008-01-17

申请号：US11812065

申请日：2007-06-14

申请人： Richard G. Stretton

发明人： Richard G. Stretton

IPC分类号： B65D85/68 ,  F16M13/00

CPC分类号： F02C7/20 ,  B64F5/50 ,  B66C1/10 ,  B66C1/107 ,  F01D25/285 ,  Y10T29/49318 ,  Y10T29/49998 ,  Y10T29/53961 ,  Y10T29/53974 ,  Y10T29/53983

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.

摘要翻译： 较大直径的燃气轮机的运输可能是有问题的。 在这种情况下，已知将风扇组件（30）与发动机芯（1）和其它部件分开以便于运输。 风扇组件（30）和发动机芯（1）的分离可能需要龙门架，这增加了不便和成本。 通过利用具有从现有的塔架（31）向下延伸的引导皮带（43）形式的悬挂构件（43）的平台（2,44），可以通过滑架台车（1）移除发动机机芯（1） 3,45），其沿着轨道（21,42）大致横向移动，直到有可能在发动机平台上降低发动机到地面平台（2,44）和托架台车（3,45） ）可以作为发动机核心运输的支架。

公开(公告)号：US20070245738A1

公开(公告)日：2007-10-25

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： F02C1/00

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：US07086219B2

公开(公告)日：2006-08-08

申请号：US11036075

申请日：2005-01-18

申请人： Richard G Stretton ,  Kenneth F Udall

发明人： Richard G Stretton ,  Kenneth F Udall

IPC分类号： B64D29/06 ,  F02K3/06

CPC分类号： B64D33/02 ,  B64D29/00 ,  B64D2033/0206 ,  B64D2033/0286 ,  F01D11/005 ,  F02C7/04 ,  F02C7/045 ,  F02K1/80 ,  F02K1/805 ,  F04D29/164 ,  F04D29/547 ,  F04D29/681 ,  Y10T137/0536

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.

摘要翻译： 用于燃气涡轮发动机（10）的整流罩结构（18）包括限定用于施加到发动机（10）的负载的第一路径的外皮（26）。 整流罩结构（18）包括限定用于负载的第二路径的内表皮（24）。 内外表面（24,26）被构造成使得主要部分的载荷沿着第一路径传递。