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    SEGMENTED MIXING DEVICE HAVING CHEVRONS FOR EXHAUST NOISE REDUCTION IN JET ENGINES
    71.
    发明申请
    SEGMENTED MIXING DEVICE HAVING CHEVRONS FOR EXHAUST NOISE REDUCTION IN JET ENGINES 有权
    在喷气发动机中具有减少排气噪声的混合装置的分离混合装置

    公开(公告)号：US20030115852A1

    公开(公告)日：2003-06-26

    申请号：US10351649

    申请日：2003-01-23

    发明人： Ronald L. Balzer

    IPC分类号： F02K001/38

    CPC分类号： B64D33/06 ,  F02K1/386 ,  F02K1/48 ,  F05D2250/11 ,  F05D2250/13 ,  F05D2250/183 ,  F05D2250/71 ,  F05D2260/96

    摘要： Disclosed is a means for reducing jet engine exhaust noise wherein mixing is enhanced between adjacent exhaust flows and between exhaust flow and free-stream flow. The device does so with a very small degradation in aircraft performance. The device is a segmented, triangular or trapezoidal shaped, curved extension to a nozzle's sleeve that results in a serrated trailing edge. The nozzle extensions enhance the natural free mixing of the jet's exhaust flows and therefore reduce the acoustic energy associated with the velocity differences between the streams in which they are imbedded. The novel structure forces adjacent flows to penetrate into one another to a greater depth than that achievable with free mixing and results in a more uniform flow in a shorter stream wise distance while limiting high frequency noise through utilization of root radii in the order of 15 to 20% of the segment's width at the intersection of a parent nozzle.

    摘要翻译： 公开了一种用于减少喷气发动机排气噪声的手段，其中在相邻排气流之间以及排气流和自由流之间的混合被增强。 该装置在飞机性能下降很小。 该装置是一个分段，三角形或梯形的弯曲的延伸到喷嘴的套筒，导致锯齿状的后缘。 喷嘴延伸部增强了射流的排气流的自然的自由混合，并因此降低了与它们嵌入的流之间的速度差有关的声能。 新颖的结构迫使相邻的流体彼此渗透到比通过自由混合可实现的深度更大的深度，并且导致在更短的流方向上的更均匀的流动，同时通过使用根部半径的约15至15的限制高频噪声 在母嘴的交点处的片段宽度的20％。

    Thrust reverser for a gas turbine engine
    72.
    发明授权
    Thrust reverser for a gas turbine engine 失效
    用于燃气轮机的推力反向器

    公开(公告)号：US06557338B2

    公开(公告)日：2003-05-06

    申请号：US09760809

    申请日：2001-01-17

    申请人： Michael J Holme ,  Jeffrey C Bishop

    发明人： Michael J Holme ,  Jeffrey C Bishop

    IPC分类号： F02K156

    CPC分类号： F02K1/54 ,  F02K1/70 ,  F05D2230/20 ,  F05D2250/183 ,  Y02T50/672 ,  Y10T428/12361 ,  Y10T428/1241

    摘要： A thrust reverser cascade flow directing element (28) for a gas turbine engine (10) comprises a plurality of plates (30) and a plurality of flow directing vanes (40). At least one vane (40) extends between each pair of plates (30), the plurality of plates (30) are formed from sheet material and a single integral piece of ductile sheet material (32) forms the plurality of flow directing vanes (40). The single integral piece of ductile sheet material (32) has a plurality of longitudinally spaced apart apertures (36) and a plurality of longitudinally spaced apart sheet material portions (38) between the apertures (36) and the ductile sheet material (32) is bent at a plurality of longitudinally spaced positions such that each sheet material portion (38) defines one of the plurality of flow directing vanes (40).

    摘要翻译： 用于燃气涡轮发动机（10）的推力反向器级联流动引导元件（28）包括多个板（30）和多个导流叶片（40）。 至少一个叶片（40）在每对板（30）之间延伸，多个板（30）由片材形成，并且单个整体的延性片材（32）形成多个导流叶片（40） ）。 延伸片材材料（32）的单个整体件具有多个纵向间隔开的孔（36），并且在孔（36）和延性片材（32）之间的多个纵向间隔开的片材部分（38） 在多个纵向间隔位置处弯曲，使得每个片材部分（38）限定多个导流叶片（40）中的一个。

    Micro-grooved heat transfer wall
    73.
    发明授权
    Micro-grooved heat transfer wall 失效
    微沟槽传热墙

    公开(公告)号：US5337568A

    公开(公告)日：1994-08-16

    申请号：US43167

    申请日：1993-04-05

    申请人： Ching-Pang Lee ,  Steven G. Goebel ,  Nesim Abuaf

    发明人： Ching-Pang Lee ,  Steven G. Goebel ,  Nesim Abuaf

    IPC分类号： F01D5/18 ,  F23R3/00 ,  F23R3/16

    CPC分类号： F01D5/18 ,  F23R3/002 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/294 ,  F05D2260/221 ,  F05D2260/2212 ,  Y02T50/676

    摘要： A gas turbine engine hot section component such as a turbine blade or vane having an airfoil is provided a non-film cooled portion of a heat transfer wall having a hot surface and a plurality of longitudinally extending micro-grooves disposed in the portion of the wall along the hot surface in a direction parallel to the direction of the hot gas flow. The depth of the micro-grooves is very small and on the order of magnitude of a predetermined laminar sublayer of a turbulent boundary layer. The grooves are sized so as to alter the boundary layer thickness near the leading edge of the airfoil to reduce heat transfer from the hot gas flow to the airfoil near the leading edge. In one embodiment the micro-grooves are about 0.001 inches deep and have a preferred depth range of from about 0.001 inches to 0.005 inches and which are square, rectangular, or triangular in cross-section and the micro-grooves are spaced about one width apart.

    摘要翻译： 具有翼型的涡轮机叶片或叶片的燃气涡轮发动机热段部件设置有具有热表面的传热壁的非薄膜冷却部分和设置在壁的部分中的多个纵向延伸的微槽 沿着热表面平行于热气流的方向。 微槽的深度非常小，并且在湍流边界层的预定层状亚层的数量级上。 这些槽的尺寸被设计成改变靠近翼型的前缘附近的边界层厚度，以减少从热气流到靠近前缘的翼型件的热传递。 在一个实施例中，微槽约为0.001英寸深，并且具有约0.001英寸至0.005英寸的优选深度范围，并且其横截面为正方形，矩形或三角形，并且微槽间隔约一分之一宽度 。

    Airfoil Trailing Edge Segment
    76.
    发明申请
    Airfoil Trailing Edge Segment 审中-公开

    公开(公告)号：US20180163552A1

    公开(公告)日：2018-06-14

    申请号：US15372859

    申请日：2016-12-08

    申请人： General Electric Company

    发明人： Brandon ALlanson Reynolds ,  Matthew Mark Weaver

    IPC分类号： F01D9/06 ,  F01D9/02

    CPC分类号： F01D9/065 ,  F01D5/282 ,  F01D5/284 ,  F01D9/02 ,  F01D9/042 ,  F02K3/04 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2250/183 ,  F05D2260/202 ,  F05D2300/6033

    摘要： Turbine nozzle sections and airfoils having trailing edge segments are provided. In one embodiment, a turbine nozzle section comprises an inner band defining a pocket; an outer band defining an opening therethrough; and an airfoil radially extending from the inner band to the outer band and including pressure and suction sides. The airfoil has a body segment including a cavity and a plurality of ejector apertures defining a passageway from the cavity to an outer surface of the airfoil, and a trailing edge segment including an inner end and an outer end. The body segment defines a projection projecting inwardly from the suction side, and the trailing edge segment defines a notch opening toward the suction side. The projection is received within the notch. The inner end of the trailing edge segment is received within the inner band pocket, and the outer end is positioned within the outer band opening.