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公开(公告)号：US20180298829A1
公开(公告)日：2018-10-18
申请号：US15490155
申请日：2017-04-18
摘要： A gas turbine engine comprises a housing having an inlet leading to a fan rotor. A bypass door is mounted upstream of the inlet to the fan rotor, and is moveable away from a non-bypass position to a bypass position to selectively bypass boundary layer air vertically beneath the engine. An aircraft is also disclosed.
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公开(公告)号：US09982689B2
公开(公告)日：2018-05-29
申请号：US14826492
申请日：2015-08-14
发明人： Matthew R. Feulner
CPC分类号： F04D29/706 , F01D9/041 , F01D25/32 , F04D29/321 , F04D29/542 , F05D2240/123 , F05D2260/602
摘要： A compressor of a gas turbine engine includes at least one rotor, and at least one stator, wherein the at least one stator includes a water channel wall located on a surface of the stator, wherein the water channel wall is configured to direct water away from a center line of the turbine engine and is located an offset distance from an outside wall of the compressor, wherein the offset distance is zero percent to twenty percent of the span of the stator.
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公开(公告)号：US20170370326A1
公开(公告)日：2017-12-28
申请号：US15194944
申请日：2016-06-28
发明人： Matthew R. Feulner
摘要： A gas turbine engine includes an engine core includes at least one compressor, a combustor downstream of the compressor, and at least one turbine downstream of the combustor. A primary flowpath fluidly connects each of the compressor, the combustor, and the turbine. At least one particle extraction duct has an extraction duct inlet connected to the primary flowpath fore of the compressor and an extraction duct outlet connected to a bypass flowpath.
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公开(公告)号：US20170327235A1
公开(公告)日：2017-11-16
申请号：US15153837
申请日：2016-05-13
发明人： Matthew R. Feulner
CPC分类号： B64D13/08 , B64D13/06 , B64D15/04 , B64D2013/0618 , B64D2013/0648 , B64F1/34 , F02C1/02 , F02C3/04 , F02C6/08 , F02C7/277 , F05D2220/32 , F05D2250/90 , F05D2260/4031 , F05D2260/606 , F05D2260/85
摘要： A dual-use air turbine system for a gas turbine engine of an aircraft is provided. The dual-use air turbine system includes a variable area air turbine mechanically linked to a spool of the gas turbine engine through a multi-speed gear set. The dual-use air turbine system also includes a plurality of valves in pneumatic ducting operable to direct an engine start air flow through an inlet of the variable area air turbine and drive rotation of the spool during an engine start mode of operation. The valves are further operable to direct an engine bleed air flow from a compressor section of the gas turbine engine through the inlet of the variable area air turbine and drive rotation of the spool during an environmental control system active mode of operation.
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公开(公告)号：US20140093350A1
公开(公告)日：2014-04-03
申请号：US13631436
申请日：2012-09-28
发明人： Richard P. Meisner , Brian V. Winebrenner , Matthew R. Feulner , Boris Karpman , Juan A. Marcos , David L. Ma
IPC分类号： F01D17/00
CPC分类号： F01D17/00 , F01D17/08 , F02C9/18 , F02C9/52 , F02C9/54 , F04D27/001 , F05D2270/101
摘要： A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to generate a real-time estimate of compressor stall margin from an engine model, and command engine actuators to correct for the difference between the real time estimate of compressor stall margin and a required stall margin.
摘要翻译： 燃气涡轮发动机包括压缩机，燃烧器，涡轮机和电子发动机控制系统。 压缩机，燃烧器和涡轮机以流动系列布置。 电子发动机控制系统被配置为从发动机模型生成压缩机失速余量的实时估计，以及指令发动机执行器，以校正压缩机失速余量的实时估计与所需失速余量之间的差异。
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