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公开(公告)号：US20070245738A1
公开(公告)日：2007-10-25
申请号：US11785590
申请日：2007-04-18
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。
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公开(公告)号：US08444085B2
公开(公告)日：2013-05-21
申请号：US13232311
申请日：2011-09-14
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。
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公开(公告)号：US20070245739A1
公开(公告)日：2007-10-25
申请号：US11785646
申请日：2007-04-19
IPC分类号： F02C1/00
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，并且设置专用的出口管道，使得来自热交换器的排出的流体流沿管道管道被输送到低压 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。
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公开(公告)号：US07861513B2
公开(公告)日：2011-01-04
申请号：US11783996
申请日：2007-04-13
申请人： Richard G. Stretton
发明人： Richard G. Stretton
IPC分类号： F02K3/02
CPC分类号： F02C7/185 , B64C7/02 , F02K3/115 , F05D2250/52 , Y02T50/675
摘要： A gas turbine engine comprising a ventilation zone defined between a core engine casing and a core fairing and having a discharge nozzle, the engine further comprises a pre-cooler having a flow of coolant therethrough and which coolant being ducted into the ventilation zone wherein an additional ventilation zone outlet system is provided and comprises a variable area outlet.
摘要翻译： 一种燃气涡轮发动机，包括限定在核心发动机壳体和芯整流装置之间并具有排放喷嘴的通气区域，发动机还包括具有冷却剂流过的预冷器，并且该冷却剂被导入通风区域，其中附加 提供通风区出口系统，并包括可变区域出口。
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公开(公告)号：US20070245711A1
公开(公告)日：2007-10-25
申请号：US11783996
申请日：2007-04-13
申请人： Richard G. Stretton
发明人： Richard G. Stretton
IPC分类号： F02K3/02
CPC分类号： F02C7/185 , B64C7/02 , F02K3/115 , F05D2250/52 , Y02T50/675
摘要： A gas turbine engine comprising a ventilation zone defined between a core engine casing and a core fairing and having a discharge nozzle, the engine further comprises a pre-cooler having a flow of coolant therethrough and which coolant being ducted into the ventilation zone wherein an additional ventilation zone outlet system is provided and comprises a variable area outlet.
摘要翻译： 一种燃气涡轮发动机，包括限定在核心发动机壳体和芯整流装置之间并具有排放喷嘴的通气区域，发动机还包括具有冷却剂流过的预冷器，并且该冷却剂被导入通风区域，其中附加 提供通风区出口系统，并包括可变区域出口。
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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）。
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公开(公告)号：US20100284790A1
公开(公告)日：2010-11-11
申请号：US12768316
申请日：2010-04-27
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。
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公开(公告)号：US20090071122A1
公开(公告)日：2009-03-19
申请号：US11363040
申请日：2006-02-28
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。
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公开(公告)号：US08967967B2
公开(公告)日：2015-03-03
申请号：US13359194
申请日：2012-01-26
CPC分类号： F01D5/022 , B64C11/48 , B64D29/00 , B64D2027/005 , F01D5/143 , F01D5/145 , F02C3/067 , F02K3/072 , F05D2220/324 , F05D2220/325 , F05D2240/14 , F05D2250/70 , Y02T50/66 , Y02T50/671
摘要： The present disclosure relates to a propfan engine comprising: one or more rotor stages comprising a plurality of rotors; and an outer wall comprising an outer profile, at least a portion of the outer profile defining a substantially circular cross-section, wherein the diameter of the substantially circular cross-section increases in the direction of flow over the outer wall and downstream of a leading edge of the rotors, and the diameter increases at substantially all points defining the circumference of the substantially circular cross-section.
摘要翻译： 本公开涉及一种普通发动机，其包括：一个或多个转子级，包括多个转子; 以及外壁，其包括外轮廓，所述外轮廓的至少一部分限定基本上圆形的横截面，其中所述基本圆形横截面的直径在所述外壁上的流动方向上增加，并且在前缘 转子的边缘，并且在限定基本圆形横截面的圆周的基本上所有点处的直径增加。
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公开(公告)号：US08434995B2
公开(公告)日：2013-05-07
申请号：US12768316
申请日：2010-04-27
IPC分类号： F01D21/00
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。
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