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1.发明申请公开(公告)号：US20170276141A1
公开(公告)日：2017-09-28
申请号：US15082524
申请日：2016-03-28
Applicant: General Electric Company
Inventor： Swati Saxena , Ajay Keshava Rao , Rudolf Konrad Selmeier , Grover Andrew Bennett , Giridhar Jothiprasad , Corey Bourassa , Byron Andrew Pritchard
CPC classification number: F02C9/18 , F02C6/08 , F04D29/542 , F05D2260/607
Abstract: A compressor assembly for a turbomachine includes a compressor wall including circumferentially spaced stator vanes defining at least one row of stator vanes. The at least one row of stator vanes defines at least one stator passage therein. Each stator vane includes a leading edge, an opposite trailing edge defining an axial chord distance, and a pressure side. The compressor assembly also includes, at least one bleed opening defined within the compressor wall and disposed adjacent the pressure side in the at least one stator passage within a range from approximately 20% the axial chord distance upstream of the leading edge to approximately 20% the axial chord distance downstream of the trailing edge. The compressor assembly further includes at least one bleed arm extending from the at least one bleed opening with at least a portion of compressor airflow extractable through the at least one bleed arm.
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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
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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公开(公告)号：US09790796B2
公开(公告)日：2017-10-17
申请号：US14031206
申请日：2013-09-19
Applicant: General Electric Company
Inventor： John David Stampfli , Ajay Keshava Rao , Rudolf Konrad Selmeier
IPC: F01D5/14
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.
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4.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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公开(公告)号：US10823194B2
公开(公告)日：2020-11-03
申请号：US14556315
申请日：2014-12-01
Applicant: General Electric Company
Inventor： Giridhar Jothiprasad , Ramakrishna Venkata Mallina , John David Stampfli , Rudolf Konrad Selmeier , Davide Giacché
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.
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Patent Agency Ranking
6.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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7.发明申请公开(公告)号：US20150075179A1
公开(公告)日：2015-03-19
申请号：US14031206
申请日：2013-09-19
Applicant: General Electric Company
Inventor： John David Stampfli , Ajay Keshava Rao , Rudolf Konrad Selmeier
IPC: F01D5/14
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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公开(公告)号：US10227930B2
公开(公告)日：2019-03-12
申请号：US15082524
申请日：2016-03-28
Applicant: General Electric Company
Inventor： Swati Saxena , Ajay Keshava Rao , Rudolf Konrad Selmeier , Grover Andrew Bennett , Giridhar Jothiprasad , Corey Bourassa , Byron Andrew Pritchard
Abstract: A compressor assembly for a turbomachine includes a compressor wall including circumferentially spaced stator vanes defining at least one row of stator vanes. The at least one row of stator vanes defines at least one stator passage therein. Each stator vane includes a leading edge, an opposite trailing edge defining an axial chord distance, and a pressure side. The compressor assembly also includes, at least one bleed opening defined within the compressor wall and disposed adjacent the pressure side in the at least one stator passage within a range from approximately 20% the axial chord distance upstream of the leading edge to approximately 20% the axial chord distance downstream of the trailing edge. The compressor assembly further includes at least one bleed arm extending from the at least one bleed opening with at least a portion of compressor airflow extractable through the at least one bleed arm.
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公开(公告)号：US20180313364A1
公开(公告)日：2018-11-01
申请号：US15499731
申请日：2017-04-27
Applicant: General Electric Company
Inventor： Curtis William Moeckel , Matthew Ford Adam , Rudolf Konrad Selmeier , Michael Anthony Thomas , Steven Mitchell Taylor , Anton Streit
Abstract: A compressor bleed slot apparatus includes: an annular compressor casing; a stator vane row including a plurality of stator vanes disposed inside the compressor casing; a blade row mounted for rotation about a centerline axis inside the compressor casing, axially downstream of the stator row; a bleed slot passing through the compressor casing, the bleed slot having an inlet and an outlet and extending along a slot axis, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the inboard and outboard walls diverging from each other in a downstream direction relative to the bleed slot; and a plurality of turning vanes disposed in the slot, the turning vanes configured to reduce a tangential velocity of airflow through the bleed slot.
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公开(公告)号：US10030669B2
公开(公告)日：2018-07-24
申请号：US14315405
申请日：2014-06-26
Applicant: General Electric Company
Inventor： Ismail Hakki Sezal , Christian Aalburg , Rajesh Kumar Venkata Gadamsetty , Matthias Carl Lang , Venkata Rama Krishna Chaitanya Ongole , Alberto Scotti del Greco , Rudolf Konrad Selmeier
Abstract: Embodiments of an apparatus for transferring energy between a rotating element and a fluid are provided herein. In some embodiments, a plenum of an apparatus for transferring energy between a rotating element and a fluid may include a through hole disposed through the plenum; and a plurality of inlet guide vanes disposed proximate a peripheral edge of the through hole, the plurality of inlet guide vanes comprising a first group of inlet guide vanes having a cambered profile and a second group of inlet guide vanes disposed radially inward of the first group of inlet guide vanes, wherein the first group of inlet guide vanes are in a fixed position with respect to the plenum and the second group of inlet guide vanes are movable with respect to the plenum.
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