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公开(公告)号：US10233841B2
公开(公告)日：2019-03-19
申请号：US14933518
申请日：2015-11-05
IPC分类号： F02C7/14 , F02C7/16 , F01D25/16 , F02K3/06 , F02C7/047 , B64D15/06 , F02C7/12 , B64D15/02 , B64D15/00 , F01D25/02
摘要： In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.
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公开(公告)号：US20160131036A1
公开(公告)日：2016-05-12
申请号：US14933518
申请日：2015-11-05
CPC分类号： F02C7/16 , B64D15/00 , B64D15/02 , B64D15/06 , F01D25/02 , F01D25/162 , F02C7/047 , F02C7/12 , F02C7/14 , F02K3/06 , F05D2220/32 , F05D2260/213 , F05D2260/98 , Y02T50/675
摘要： In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.
摘要翻译： 在一个示例性实施例中，用于冷却发动机部件的燃气涡轮发动机系统包括发动机芯，容纳发动机芯的铁芯壳体，芯壳体前方的发动机芯驱动风扇，围绕风扇和芯壳体的机舱，以及 旁通管道限定在芯壳体的外径和机舱的内径之间。 还包括一种具有冷却剂回路的热管理系统，该冷却剂回路包括设置在机舱内径上的第一热交换器和布置在跨过旁通管的BiFi前缘的第二热交换器中的至少一个。 第一热交换器与第二热交换器热连通。
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公开(公告)号：US11047397B2
公开(公告)日：2021-06-29
申请号：US15110889
申请日：2014-12-26
摘要： A gas turbine engine includes a circumferential array of stator vanes that have first and second vanes with different vibrational frequencies than one another. The first vanes are arranged in circumferentially alternating relationship with the second vanes.
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公开(公告)号：US20170254208A1
公开(公告)日：2017-09-07
申请号：US15058892
申请日：2016-03-02
CPC分类号： F01D5/148 , B29C35/02 , B29C65/48 , B29C66/742 , B29C70/865 , B29C70/88 , B29D99/0025 , B29K2305/00 , B29L2031/082 , F01D5/141 , F01D5/147 , F01D5/282 , F03G7/065 , F05D2220/36 , F05D2300/505 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.
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公开(公告)号：US20200032655A1
公开(公告)日：2020-01-30
申请号：US16431403
申请日：2019-06-04
IPC分类号： F01D5/14 , B29C70/86 , B29C70/88 , B29D99/00 , B29C35/02 , B29C65/48 , B29C65/00 , F01D5/28 , F03G7/06
摘要： An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.
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公开(公告)号：US10801336B1
公开(公告)日：2020-10-13
申请号：US15869290
申请日：2018-01-12
发明人： Charles P. Gendrich , Christopher St. Mary , Xuedong Zhou , Joseph Wieser , Zhen Wu , John Joseph Papalia , Kaliya Balamurugan , Joseph Steele , Jeff M. Carrico , Danoris Garcia-Chabrier
摘要： An airfoil has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.70-0.83 inch (17.8-21.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.34-0.45 inch (8.5-11.5 mm). The airfoil element includes at least three of a first mode with a frequency of 3748±15% Hz, a second mode with a frequency of 6416±15% Hz, a third mode with a frequency of 14418±15% Hz, a fourth mode with a frequency of 17417±15% Hz, a fifth mode with a frequency of 19326±15% Hz and a sixth mode with a frequency of 26648±15% Hz.
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公开(公告)号：US10352173B2
公开(公告)日：2019-07-16
申请号：US15058892
申请日：2016-03-02
IPC分类号： F01D5/14 , B29C35/02 , B29D99/00 , B29C70/88 , B29C70/86 , B29C65/48 , B29C65/00 , F01D5/28 , F03G7/06 , B29K305/00 , B29L31/08
摘要： An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.
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