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公开(公告)号：US20170089217A1
公开(公告)日：2017-03-30
申请号：US14870300
申请日：2015-09-30
Applicant: General Electric Company
Inventor： Swati Saxena , Andrew Breeze-Stringfellow , Rajkeshar Vijayraj Singh , Tsuguji Nakano
CPC classification number: F04D27/02 , F01D25/02 , F02C3/04 , F04D29/526 , F04D29/681 , F05D2220/32 , F05D2220/3219 , F05D2250/294
Abstract: A compressor is provided including a casing, a hub, a flowpath, a plurality of blades defining a plurality of axially extending compressor stages and an endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages. The remaining stages of the plurality of compressor stages located upstream of the at least two downstream most stage are devoid of any endwall treatment. Each of the endwall treatments faces a tip of each blade in the at least two downstream most stages. The tip of each blade and the endwall treatment are configured to move relative to each other. The endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages is configured to extend a stall margin to delay stall due to ice ingestion. A method and engine application are disclosed.
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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：US10132323B2
公开(公告)日：2018-11-20
申请号：US14870300
申请日：2015-09-30
Applicant: General Electric Company
Inventor： Swati Saxena , Andrew Breeze-Stringfellow , Rajkeshar Vijayraj Singh , Tsuguji Nakano
Abstract: A compressor is provided including a casing, a hub, a flowpath, a plurality of blades defining a plurality of axially extending compressor stages and an endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages. The remaining stages of the plurality of compressor stages located upstream of the at least two downstream most stage are devoid of any endwall treatment. Each of the endwall treatments faces a tip of each blade in the at least two downstream most stages. The tip of each blade and the endwall treatment are configured to move relative to each other. The endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages is configured to extend a stall margin to delay stall due to ice ingestion. A method and engine application are disclosed.
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4.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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