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公开(公告)号：US10539154B2
公开(公告)日：2020-01-21
申请号：US15531992
申请日：2014-12-10
Applicant: General Electric Company
Inventor： Ramakrishna Venkata Mallina , Sungho Yoon , Vittorio Michelassi , Ivan Malcevic
Abstract: A compressor is provided including a compressor end-wall having a casing and a hub. The compressor further includes at least one set of rotor blades, one set of stator blades, and a plurality of end-wall treatments spaced apart from each other, formed in an interior surface of at least one of the casing and hub, and facing a tip of the rotor blade or stator blade. Each end-wall treatment includes a forward recess portion extending along a first axis and an aft recess portion extending along a second axis different than the first axis. The aft recess portion is joined to the corresponding forward recess portion via an intersection portion which is inclined relative to at least one of the first axis, and the second axis. The aft recess portion and/or the forward recess portion are bent from the intersection portion and inclined relative to an axial direction of the compressor.
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2.发明授权公开(公告)号：US10047620B2
公开(公告)日：2018-08-14
申请号：US14572119
申请日：2014-12-16
Applicant: General Electric Company
Inventor： Davide Giacché , John David Stampfli , Ramakrishna Venkata Mallina , Vittorio Michelassi , Giridhar Jothiprasad , Ajay Keshava Rao , Rudolf Konrad Selmeier , Sungho Yoon , Ivan Malcevic
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.
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3.发明申请公开(公告)号：US20160153465A1
公开(公告)日：2016-06-02
申请号：US14556452
申请日：2014-12-01
Applicant: General Electric Company
Inventor： Sungho Yoon , John David Stampfli , Ramakrishna Venkata Mallina , Vittorio Michelassi , Giridhar Jothiprasad , Ajay Keshava Rao , Rudolf Konrad Selmeier , Davide Giacché , Ivan Malcevic
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。
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4.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
Applicant: General Electric Company
Inventor： Davide Giacché , John David Stampfli , Ramakrishna Venkata Mallina , Vittorio Michelassi , Giridhar Jothiprasad , Ajay Keshava Rao , Rudolf Konrad Selmeier , Sungho Yoon , Ivan Malcevic
CPC classification number: F01D11/001 , F04D27/02 , F04D29/526 , F04D29/68 , F04D29/681 , F04D29/685
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。
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