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公开(公告)号：US10457401B2
公开(公告)日：2019-10-29
申请号：US15153837
申请日：2016-05-13
发明人： Matthew R. Feulner
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：US10330010B2
公开(公告)日：2019-06-25
申请号：US14967518
申请日：2015-12-14
发明人： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler , William K. Ackermann , Matthew R. Feulner , Om P. Sharma
摘要： A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
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公开(公告)号：US10293951B2
公开(公告)日：2019-05-21
申请号：US15072869
申请日：2016-03-17
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a control unit to command the gas turbine engine to perform one of a rolling takeoff procedure and an unrestricted takeoff procedure. The control unit is configured command the gas turbine engine to perform the rolling takeoff procedure when information required to determine whether the unrestricted takeoff procedure can be performed is unavailable to the control unit.
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公开(公告)号：US20170342913A1
公开(公告)日：2017-11-30
申请号：US15162727
申请日：2016-05-24
发明人： Matthew R. Feulner
CPC分类号： F02C9/48 , F02C3/04 , F02C7/04 , F02C7/32 , F02C9/28 , F05D2220/32 , F05D2270/3013 , F05D2270/304 , F05D2270/312 , F05D2270/313 , F05D2270/71 , F05D2270/80 , G01K7/427 , G01K13/02 , G01K2013/024
摘要： A gas turbine engine including a compressor, a combustor fluidly connected to the compressor via a primary flowpath, a turbine fluidly connected to the combustor via the primary flowpath, an engine controller communicatively coupled to at least one sensor in the gas turbine engine, the controller including a non-transitory memory and a processor, and the at least one sensor including an inlet temperature and/or pressure sensor, wherein the sensor is disposed aft of a fan.
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公开(公告)号：US20170267366A1
公开(公告)日：2017-09-21
申请号：US15072869
申请日：2016-03-17
CPC分类号： B64D31/06 , B64D27/10 , B64D31/12 , F02C9/28 , F05D2270/051 , F05D2270/102 , F05D2270/1022 , G05D1/0661
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a control unit to command the gas turbine engine to perform one of a rolling takeoff procedure and an unrestricted takeoff procedure. The control unit is configured command the gas turbine engine to perform the rolling takeoff procedure when information required to determine whether the unrestricted takeoff procedure can be performed is unavailable to the control unit.
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公开(公告)号：US20170234236A1
公开(公告)日：2017-08-17
申请号：US15042382
申请日：2016-02-12
CPC分类号： F02C7/277 , F01D19/02 , F02C7/18 , F02C9/00 , F05D2260/20 , F05D2260/85 , F05D2260/96 , F05D2270/02 , F05D2270/114 , Y02T50/676
摘要： A bowed rotor start mitigation system for a gas turbine engine is provided. The bowed rotor start mitigation system includes a variable position starter valve and a controller. The controller is operable to dynamically adjust the variable position starter valve to deliver a starter air supply to a starter to drive rotation of a starting spool of the gas turbine engine according to a dry motoring profile that continuously varies a rotor speed of the starting spool up to a point below a critical rotor speed.
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公开(公告)号：US20170167384A1
公开(公告)日：2017-06-15
申请号：US14967518
申请日：2015-12-14
发明人： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler , William K. Ackermann , Matthew R. Feulner , Om P. Sharma
CPC分类号： F02C7/18 , F01D5/08 , F02C3/04 , F02C7/143 , F02C7/185 , F02C9/18 , F02K3/06 , F04D27/0215 , F04D29/582 , F05D2220/32 , F05D2220/3219 , F05D2240/24 , F05D2260/205 , F05D2260/211 , F05D2260/213 , Y02T50/676
摘要： A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
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28.发明申请APPARATUS AND METHOD FOR WATER AND ICE FLOW MANAGEMENT IN A GAS TURBINE ENGINE 有权燃气涡轮发动机水和冰流量管理的装置和方法公开(公告)号：US20170045061A1
公开(公告)日：2017-02-16
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.
摘要翻译： 燃气涡轮发动机的压缩机包括至少一个转子和至少一个定子，其中所述至少一个定子包括位于所述定子的表面上的水通道壁，其中所述水通道壁被构造成将水引导离开 涡轮发动机的中心线并且位于距离压缩机的外壁的偏移距离处，其中偏移距离为定子跨度的零百分之二十。
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公开(公告)号：US11473510B2
公开(公告)日：2022-10-18
申请号：US16388227
申请日：2019-04-18
发明人： Joseph Kehoe , Richard P. Meisner , Manuj Dhingra , Patrick D. Couture , Matthew R. Feulner , Brenda J. Lisitano , Christopher L. Ho
摘要： A method of operating a gas turbine engine includes commanding an acceleration of the gas turbine engine and moving a variable pitch high pressure compressor vane toward an open position thereby reducing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal. An active clearance control system of a gas turbine engine includes an engine control system configured to command an acceleration of the gas turbine engine and move a variable pitch high pressure compressor vane toward an open position thereby slowing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal located radially outboard of the high pressure turbine rotor.
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公开(公告)号：US11339678B2
公开(公告)日：2022-05-24
申请号：US16039475
申请日：2018-07-19
发明人： Matthew R. Feulner
摘要： A system for controlling blade tip clearances in a gas turbine engine may comprise an active clearance control system and a controller in operable communication with the active clearance control system. The controller may be configured to identify a cruise condition, reduce a thrust limit of the gas turbine engine to a de-rated maximum climb thrust, determine a first target tip clearance based on the de-rated maximum climb thrust, and send a command signal correlating to the first target tip clearance to the active clearance control system.
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