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Patent Agency Ranking1.发明申请
公开(公告)号：WO2018144080A1
公开(公告)日：2018-08-09
申请号：PCT/US2017/056849
申请日：2017-10-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： HURT, Matthew, John , PEREZ VALADEZ, Alejandro, Yatzail , BRINSON, Thomas, Edward , CERNY, Matthew, Robert , MISRA MARTINEZ, Amit, Kumar , PARKER, David, Vickery , CARITA, Robert, Gregory
Abstract: Systems and methods for integrated power and thermal management in a turbine-powered aircraft are provided. The systems may include rotationally-independent first and second auxiliary power unit shafts, a power turbine, a first compressor, a second compressor, a cooling turbine, and an electrical motor-generator. The power turbine may be rotatably disposed on the first auxiliary power unit shaft. The first compressor may be rotatably disposed on the first auxiliary power unit shaft. The second compressor may be rotatably disposed on the second auxiliary power unit shaft. The cooling turbine may be rotatably disposed on the second auxiliary power unit shaft. The electrical motor-generator may disposed on the first auxiliary power unit shaft to alternatively supply a motive force input to the first auxiliary power unit shaft and an electrical power output to the aircraft.
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2.发明申请
公开(公告)号：WO2016039918A1
公开(公告)日：2016-03-17
申请号：PCT/US2015/044709
申请日：2015-08-11
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F04D29/462 , F01D17/162 , F02C3/04 , F04D17/025 , F04D19/02 , F04D29/403 , F04D29/4213 , F04D29/563 , F05D2220/32 , F05D2240/35
Abstract: A compressor apparatus includes: an upstream portion comprising an axial-flow compressor; a downstream portion comprising a centrifugal-flow compressor; and a row of variable-stagger-angle outlet guide vanes disposed between the upstream and downstream portions.
Abstract translation: 压缩机装置包括：包括轴流式压缩机的上游部分; 包括离心流压缩机的下游部分; 以及设置在上游部分和下游部分之间的一排可变交错角出口导向叶片。
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3.发明申请
公开(公告)号：WO2018144080A8
公开(公告)日：2018-08-09
申请号：PCT/US2017/056849
申请日：2017-10-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： HURT, Matthew, John , CARITA, Robert, Gregory , BRINSON, Thomas, Edward , CERNY, Matthew, Robert , MISRA MARTINEZ, Amit, Kumar , PARKER, David, Vickery , PEREZ VALADEZ, Alejandro, Yatzail
Abstract: Systems and methods for integrated power and thermal management in a turbine-powered aircraft are provided. The systems may include rotationally-independent first and second auxiliary power unit shafts, a power turbine, a first compressor, a second compressor, a cooling turbine, and an electrical motor-generator. The power turbine may be rotatably disposed on the first auxiliary power unit shaft. The first compressor may be rotatably disposed on the first auxiliary power unit shaft. The second compressor may be rotatably disposed on the second auxiliary power unit shaft. The cooling turbine may be rotatably disposed on the second auxiliary power unit shaft. The electrical motor-generator may disposed on the first auxiliary power unit shaft to alternatively supply a motive force input to the first auxiliary power unit shaft and an electrical power output to the aircraft.
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公开(公告)号：WO2015102727A1
公开(公告)日：2015-07-09
申请号：PCT/US2014/061020
申请日：2014-10-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： PARKER, David, Vickery , MACRORIE, Michael , SMYTHE, Caittlin, Jeanne , MILLER, David, Paul
CPC classification number: F04D29/444 , F01D9/02 , F05D2250/324
Abstract: A diffuser (42) for a centrifugal compressor (18) including an annular diffuser housing (20) having a plurality of diffuser flow passages (22) therethrough the housing (20). Each passage (22) including a throat portion (28) and a diffusing section (99) with upstream and downstream diffusing portions (102, 104). A diffusing passage centerline (108) includes a linear portion (120) extending downstream through the throat portion (28) and the upstream diffusing portion (102) and a curved portion (122) of the diffusing passage centerline (108) extending downstream from the centerline linear portion (120) through the downstream diffusing portion (104). The diffuser flow passages (22) may have an equivalent cone angle (CA2) varying non-linearly or more particularly curvilinearly downstream along curved portion (122). The downstream diffusing portion (104) may be flared.
Abstract translation: 一种用于离心压缩机（18）的扩散器（42），其包括环形扩散器壳体（20），其具有穿过所述壳体（20）的多个扩散器流动通道（22）。 每个通道（22）包括具有上游和下游扩散部分（102,104）的喉部（28）和扩散部分（99）。 扩散通道中心线（108）包括在下游延伸穿过喉部（28）和上游扩散部分（102）的直线部分（120）和扩散通道中心线（108）的弯曲部分（122） 中心线线性部分（120）穿过下游扩散部分（104）。 扩散器流动通道（22）可以具有沿着弯曲部分（122）非线性地或更特别地曲线地沿下游改变的等效锥角（CA2）。 下游扩散部分（104）可以展开。
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公开(公告)号：WO2014078121A1
公开(公告)日：2014-05-22
申请号：PCT/US2013/068421
申请日：2013-11-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： CAPOZZI, Joseph , PARKER, David, Vickery , CARNES, Jeffrey, Daniel
CPC classification number: F01D9/00 , F01D5/143 , F01D17/162
Abstract: A contoured stator shroud has a stator chord overhang having a surface which varies in elevation forming a plurality of surface contours, wherein the contours reduce clearance between adjacent vanes during off design performance positioning of the vanes.
Abstract translation: 成型定子护罩具有定子弦突出端，其具有在仰角上变化的表面形成多个表面轮廓，其中轮廓在叶片的非设计性能定位期间减小相邻叶片之间的间隙。
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