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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：US20210277833A1
公开(公告)日：2021-09-09
申请号：US16809150
申请日：2020-03-04
Applicant: General Electric Company
Inventor： Veerappan Muthaiah , Ajay Keshava Rao , Timothy Andrew Healy
IPC: F02C9/20
Abstract: Systems, program products, and methods for adjusting operating limit (OL) thresholds for compressors of gas turbine systems based on mass flow loss are disclosed herein. The systems may include at least one computing device in communication with the gas turbine system, sensor(s) measuring operational characteristic(s) of the gas turbine system, and a pressure sensor measuring an ambient fluid pressure surrounding the gas turbine system. The computing device(s) may be configured to adjust operational parameters of the gas turbine system by performing processes including determining a mass flow loss between an estimated, first mass flow rate and a calculated, second mass flow rate for the compressor of the gas turbine system, and adjusting an OL threshold for the compressor of the gas turbine system based on the mass flow loss. The OL threshold for the compressor may be below a predetermined surge threshold for the compressor.
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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：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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Patent Agency Ranking
6.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：US11149654B2
公开(公告)日：2021-10-19
申请号：US16809150
申请日：2020-03-04
Applicant: General Electric Company
Inventor： Veerappan Muthaiah , Ajay Keshava Rao , Timothy Andrew Healy
IPC: F02C9/20
Abstract: Systems, program products, and methods for adjusting operating limit (OL) thresholds for compressors of gas turbine systems based on mass flow loss are disclosed herein. The systems may include at least one computing device in communication with the gas turbine system, sensor(s) measuring operational characteristic(s) of the gas turbine system, and a pressure sensor measuring an ambient fluid pressure surrounding the gas turbine system. The computing device(s) may be configured to adjust operational parameters of the gas turbine system by performing processes including determining a mass flow loss between an estimated, first mass flow rate and a calculated, second mass flow rate for the compressor of the gas turbine system, and adjusting an OL threshold for the compressor of the gas turbine system based on the mass flow loss. The OL threshold for the compressor may be below a predetermined surge threshold for the compressor.
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8.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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9.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：US20140205440A1
公开(公告)日：2014-07-24
申请号：US13744866
申请日：2013-01-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ajay Keshava Rao , Hrishikesh Vishvas Deo
CPC classification number: F01D25/00 , F01D11/001 , F05D2240/59 , F05D2250/75 , F16J15/3292 , Y10T29/4932
Abstract: A seal assembly for rotary machine is provided. The seal assembly includes multiple compliant plates disposed between a stationary component and a rotary component of the rotary machine, and coupled circumferentially along the stationary component. Each compliant plate comprises a tip configured to be disposed facing the rotary component, and at least one plate slot extending from the stationary component towards the rotary component. The seal assembly also includes at least one annular resistance member configured to be coupled to the stationary component and disposed in the at least one plate slot in the compliant plates and one or more rotor slots or grooves located circumferentially on a surface of the rotary component proximate the tip of each of the plurality of compliant plates.
Abstract translation: 提供了一种用于旋转机器的密封组件。 密封组件包括设置在旋转机器的固定部件和旋转部件之间并且沿着固定部件圆周地连接的多个柔性板。 每个柔性板包括构造成面向旋转部件设置的尖端以及从固定部件向旋转部件延伸的至少一个板槽。 密封组件还包括至少一个环形阻力构件，其构造成联接到固定部件并且设置在顺应性板中的至少一个板槽中，以及位于旋转部件的表面上周向定位的一个或多个转子槽或槽 多个柔性板中的每一个的尖端。
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