CIRCUMFERENTIALLY VARYING AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN
    2.
    发明申请
    CIRCUMFERENTIALLY VARYING AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN 审中-公开
    循环式轴流式压缩机终端处理,用于控制泄漏流量

    公开(公告)号:US20160169017A1

    公开(公告)日:2016-06-16

    申请号:US14572119

    申请日:2014-12-16

    Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.

    Abstract translation: 一种用于燃气涡轮发动机的压缩机,其包括用于控制压缩机中的泄漏流动和周向流动不均匀性的一个或多个端壁处理。 压缩机包括壳体,毂,形成在壳体和轮毂之间的流动路径,位于流动路径中的多个叶片,以及形成在至少一个的内表面中的一个或多个周向变化的端壁处理 套管或轮毂。 一个或多个周向变化的端壁处理中的每一个基于它们与紧邻的上游bladerow的相对位置周向地变化。 一个或多个端壁处理中的每一个在相对于直接相邻的上游bladerow的放置中的至少一个中或在限定多个周向变化的端壁处理中的每一个的几何参数中的周向变化。 另外公开了一种包括压缩机的发动机。

    AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN
    4.
    发明申请
    AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN 审中-公开
    用于控制泄漏流量的轴流式压缩机末端处理

    公开(公告)号:US20160153465A1

    公开(公告)日:2016-06-02

    申请号:US14556452

    申请日:2014-12-01

    CPC classification number: F04D29/526 F04D29/321 F04D29/522 F04D29/685

    Abstract: An axial compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow in the compressor. The one or more endwall treatments having a height formed in an interior surface of a compressor casing or a compressor hub and configured to return a flow adjacent a plurality of rotor blade tips or a plurality of stator blade tips to a cylindrical flow passage upstream of a point of removal of the flow. Each of the endwall treatments defining a front wall, a rear wall, an outer wall extending between the front wall and the rear wall, an axial overhang, an axial overlap, an axial lean angle and a tangential lean angle. The axial overhang extending upstream to overhang at least one of the at least one set of rotor blades or the at least one set of stator blades. The axial overlap extending downstream to overlap at least one of the at least one set of rotor blades or the at least one set of stator blades.

    Abstract translation: 一种用于燃气涡轮发动机的轴向压缩机,包括用于控制压缩机中的泄漏流的一个或多个端壁处理。 所述一个或多个端壁处理具有形成在压缩机壳体或压缩机毂的内表面中的高度,并且被配置为将邻近多个转子叶片尖端或多个定子叶片尖端的流返回到一个圆柱形流动通道 清除流量点。 每个端壁处理限定了前壁,后壁,在前壁和后壁之间延伸的外壁,轴向突出,轴向重叠,轴向倾斜角和切向倾斜角。 所述轴向突出部在所述至少一组所述转子叶片或所述至少一组定子叶片中的至少一个的上游延伸。 在下游延伸的轴向重叠与所述至少一组转子叶片或至少一组定子叶片中的至少一个重叠。

    Compressor end-wall treatment with multiple flow axes

    公开(公告)号:US10823194B2

    公开(公告)日:2020-11-03

    申请号:US14556315

    申请日:2014-12-01

    Abstract: A compressor is provided including a casing, a hub, a flow path, a plurality of blades, and an end-wall treatment formed in at least one of the casing and the hub, and facing a tip of each blade. The flow path is formed between the casing and the hub, and the plurality of blades is positioned in the flow path. The tip of each blade and the end-wall treatment are configured to move relative to each other. Such end-wall treatment includes a first recess portion extending along a first axis to maintain a fluid flow substantially straight through the first recess portion. The end-wall treatment further includes a plurality of second recess portions spaced apart from each other and extending from the first recess portion along a second axis different than the first axis to maintain the fluid flow substantially straight through the plurality of second recess portions.

    Systems and Methods for Modifying a Pressure Side on an Airfoil About a Trailing Edge
    7.
    发明申请
    Systems and Methods for Modifying a Pressure Side on an Airfoil About a Trailing Edge 有权
    关于翼缘上的压力侧修改的系统和方法

    公开(公告)号:US20150075179A1

    公开(公告)日:2015-03-19

    申请号:US14031206

    申请日:2013-09-19

    CPC classification number: F01D5/14 F01D5/141 F05D2250/712 F05D2250/713

    Abstract: An airfoil is disclosed herein. The airfoil may include a leading edge, a trailing edge, a suction side defined between the leading edge and the trailing edge, and a pressure side defined between the leading edge and the trailing edge opposite the suction side. The pressure side may include a concave profile about the trailing edge that varies from a profile of a remainder of the pressure side.

    Abstract translation: 本文公开了一种翼型件。 翼型件可以包括前缘,后缘,限定在前缘和后缘之间的吸力侧,以及限定在前缘和与吸力侧相对的后缘之间的压力侧。 压力侧可以包括围绕后缘的凹形轮廓,其与压力侧的剩余部分的轮廓不同。

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