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公开(公告)号：US10408217B2
公开(公告)日：2019-09-10
申请号：US15070268
申请日：2016-03-15
摘要： An apparatus and method of controlling a multi-stage compressor of a gas turbine engine having a front-block of stages with variable stator vanes (VSVs), a rear block of stages downstream of the front-block, and a bleed air off-take from at least one of the stages. The method includes sensing the pressure of the bleed air from the bleed air off-take and adjusting the position of the VSV for the front-block.
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公开(公告)号：US10883515B2
公开(公告)日：2021-01-05
申请号：US15601674
申请日：2017-05-22
发明人： David Paul Lurie , Sherif Alykadry Abdelfattah , Michael Julian Castillo , Anthony Louis DiPietro, Jr. , Aspi Rustom Wadia , Eric Andrew Falk , William Joseph Solomon , Andrew Breeze-Stringfellow
摘要： An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a row of vane pairs including a first row of main vanes extending radially inwardly from a stationary casing member and spaced circumferentially about a first axial location of the stationary casing member. The apparatus also includes a second row of auxiliary vanes extending radially inwardly from the stationary casing member and spaced circumferentially about a second axial location of the stationary casing member. The apparatus also includes a flow channel defined between a pressure side of each auxiliary vane and a suction side of an adjacent main vane proximate a leading edge of the adjacent main vane.
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公开(公告)号：US10221859B2
公开(公告)日：2019-03-05
申请号：US15018126
申请日：2016-02-08
发明人： Curtis William Moeckel , Peter John Wood , Matthew Ford Adam , Eric Andrew Falk , Mark Joseph Stecher
IPC分类号： F04D29/32
摘要： An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep angles for the leading edge and the trailing edge from 50% span to the tip and can have decreasing leading and trailing edge dihedral angles from 50% span to the tip.
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公开(公告)号：US20180335051A1
公开(公告)日：2018-11-22
申请号：US15601674
申请日：2017-05-22
发明人： David Paul Lurie , Sherif Alykadry Abdelfattah , Michael Julian Castillo , Anthony Louis DiPietro, JR. , Aspi Rustom Wadia , Eric Andrew Falk , William Joseph Solomon , Andrew Breeze-Stringfellow
CPC分类号： F04D29/542 , F01D9/041 , F05D2220/30 , F05D2240/12 , F05D2250/30
摘要： An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a row of vane pairs including a first row of main vanes extending radially inwardly from a stationary casing member and spaced circumferentially about a first axial location of the stationary casing member. The apparatus also includes a second row of auxiliary vanes extending radially inwardly from the stationary casing member and spaced circumferentially about a second axial location of the stationary casing member. The apparatus also includes a flow channel defined between a pressure side of each auxiliary vane and a suction side of an adjacent main vane proximate a leading edge of the adjacent main vane.
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公开(公告)号：US20170268520A1
公开(公告)日：2017-09-21
申请号：US15070268
申请日：2016-03-15
CPC分类号： F04D27/002 , F02C9/18 , F02C9/20 , F04D27/001 , F04D27/0223 , F04D27/023 , F04D27/0246 , F05D2220/32 , F05D2220/3219 , F05D2270/1024 , F05D2270/3011 , F05D2270/3013 , F05D2270/3015 , F05D2270/304
摘要： An apparatus and method of controlling a multi-stage compressor of a gas turbine engine having a front-block of stages with variable stator vanes (VSVs), a rear block of stages downstream of the front-block, and a bleed air off-take from at least one of the stages. The method includes sensing the pressure of the bleed air from the bleed air off-take and adjusting the position of the VSV for the front-block.
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公开(公告)号：US20170227016A1
公开(公告)日：2017-08-10
申请号：US15018126
申请日：2016-02-08
发明人： Curtis William Moeckel , Peter John Wood , Matthew Ford Adam , Eric Andrew Falk , Mark Joseph Stecher
IPC分类号： F04D29/32
CPC分类号： F04D29/324 , F01D5/141 , F05D2240/303 , F05D2240/304 , Y02T50/673
摘要： An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep angles for the leading edge and the trailing edge from 50% span to the tip and can have decreasing leading and trailing edge dihedral angles from 50% span to the tip.
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