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公开(公告)号：US09945246B2
公开(公告)日：2018-04-17
申请号：US15021071
申请日：2014-09-10
申请人： TURBOMECA
IPC分类号： F01D19/00 , G01M13/00 , F01D21/00 , F02C7/26 , F02C7/268 , F02C7/275 , F02C7/22 , F02C7/28 , F23R3/38
CPC分类号： F01D21/003 , F02C7/222 , F02C7/26 , F02C7/268 , F02C7/275 , F02C7/28 , F05D2220/30 , F05D2240/60 , F05D2260/80 , F05D2260/85 , F23R3/38
摘要： The invention relates to a method (1000) for monitoring a degree of coking at the dynamic seals of a turbine engine comprising: a gas generator, comprising a rotary shaft and an injection wheel mounted on said shaft, an injection manifold, dynamic seals for ensuring a seal between the injection wheel and the injection manifold, and a starter, the method comprising the steps: measuring (1500), during a phase for initiating rotation of the shaft of the gas generator by the starter, a current flowing through the starter and a voltage on the terminals of the starter, determining (1600), from the measured current and voltage, a degree of coking at the dynamic seals. The invention also relates to a turbine engine comprising a system for monitoring a degree of coking.
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公开(公告)号：US20180058257A1
公开(公告)日：2018-03-01
申请号：US15795831
申请日：2017-10-27
发明人： Denman H. James
CPC分类号： F01D21/003 , F02C3/04 , F02C7/06 , F02C7/26 , F02D41/26 , F05D2260/80 , F05D2260/85 , F05D2270/301 , F05D2270/304
摘要： An engine health monitoring system includes an engine component having a sensor system configured to monitor at least one parameter of the component. An autonomous monitoring system is coupled to the sensor system and is configured to receive and store the at least one monitored parameter while an engine controller is unpowered. The engine controller is communicatively coupled to the autonomous monitoring system.
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公开(公告)号：US20180023479A1
公开(公告)日：2018-01-25
申请号：US15216168
申请日：2016-07-21
发明人： Jesse W. Clauson , David Gelwan
CPC分类号： F02C7/27 , B64D27/12 , F01D17/145 , F01D19/00 , F01D19/02 , F01D21/003 , F01D21/02 , F02C7/277 , F05D2220/32 , F05D2220/50 , F05D2260/85 , F05D2270/114
摘要： A system for motoring a gas turbine engine of an aircraft is provided. The system includes an air turbine starter, a starter air valve operable to deliver compressed air to the air turbine starter, and a controller. The controller is operable to control motoring of the gas turbine engine, detect a fault condition that prevents the controller from maintaining a motoring speed below a threshold level, and command a mitigation action that reduces delivery of the compressed air to the air turbine starter based on detection of the fault condition.
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公开(公告)号：US20180023413A1
公开(公告)日：2018-01-25
申请号：US15656444
申请日：2017-07-21
CPC分类号： F01D19/02 , B64D27/12 , B64D41/00 , B64D2041/002 , B64F1/364 , F01D25/34 , F02C3/04 , F02C6/20 , F02C7/277 , F02C9/00 , F05D2220/323 , F05D2220/50 , F05D2260/85 , F05D2270/303
摘要： A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.
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公开(公告)号：US20180022465A1
公开(公告)日：2018-01-25
申请号：US15652692
申请日：2017-07-18
CPC分类号： B64D31/12 , F01D19/02 , F02C7/27 , F02C7/277 , F02C9/00 , F02C9/18 , F05D2220/323 , F05D2220/50 , F05D2240/40 , F05D2260/85 , F05D2270/304
摘要： A system is provided for alternating starter use during multi-engine motoring in an aircraft. The system includes a first engine starting system of a first engine and a controller. The controller is operable to coordinate control of the first engine starting system to alternate use of power from a power source relative to use of the power by one or more other engine starting systems of the aircraft while maintaining a starting spool speed of the first engine below a resonance speed of the starting spool during motoring of the first engine.
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公开(公告)号：US09874149B2
公开(公告)日：2018-01-23
申请号：US14426310
申请日：2013-08-27
申请人： Turbomeca
CPC分类号： F02C7/268 , F01D19/00 , F02C7/264 , F02C7/275 , F05D2260/85 , F05D2270/04 , F05D2270/304 , F05D2270/309
摘要： The invention relates to a method for starting an aircraft turboshaft engine, said turboshaft engine comprising a combustion chamber, a compressor shaft on which a compressor wheel is mounted to feed compressed air to said combustion chamber, at least one starter connected to said shaft so as to provide it with a specified starting torque for driving it in rotation. The method comprises accelerating the compressor shaft during a first start-up phase, then stabilizing the rotational speed of the compressor shaft during a second start-up phase. During acceleration of the compressor shaft, the rotational speed of the shaft is regulated such that the acceleration of the shaft remains substantially constant.
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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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38.发明申请公开(公告)号：US20170314420A1
公开(公告)日：2017-11-02
申请号：US15523441
申请日：2015-10-28
CPC分类号： F01K13/02 , F01K7/16 , F01K11/02 , F01K25/02 , F01K25/103 , F04D15/0011 , F04D15/0072 , F05D2260/85
摘要： Aspects of the invention generally provide a heat engine system and a method for activating a turbopump within the heat engine system during a start-up process. The heat engine system utilizes a working fluid circulated within a working fluid circuit for capturing thermal energy. In one exemplary aspect, a start-up process for a turbopump in the heat engine system is provided such that the turbopump achieves self-sustained operation in a supercritical Rankine cycle. Bypass and check valves of a start pump and the turbopump, a drive turbine throttle valve, and other valves, lines, or pumps within the working fluid circuit are controlled during the turbopump start-up process. A process control system may utilize advanced control techniques of the control sequence to provide a successful start-up process of the turbopump without over pressurizing the working fluid circuit or damaging the turbopump via low bearing pressure.
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公开(公告)号：US20170301609A1
公开(公告)日：2017-10-19
申请号：US15465234
申请日：2017-03-21
申请人： ROLLS-ROYCE plc
发明人： Kalyani G. MENON , Richard HARWOOD
IPC分类号： H01L23/473 , B64F1/34 , H05K5/06 , H05K5/03 , H05K5/02 , H02M7/00 , H05K7/20 , F02C7/12 , F02C7/26 , H01L23/053 , H01L23/08 , H01L23/10 , H01L23/467 , H01L23/00 , H01L25/07 , H01L25/11
CPC分类号： H01L23/473 , B64F1/34 , F02C7/12 , F02C7/26 , F05D2220/323 , F05D2260/85 , H01L23/053 , H01L23/08 , H01L23/10 , H01L23/467 , H01L24/32 , H01L25/072 , H01L25/115 , H01L2224/32245 , H01L2224/48091 , H01L2224/48247 , H01L2224/73265 , H01L2224/83801 , H01L2224/8384 , H01L2924/15724 , H01L2924/15747 , H02M7/003 , H05K5/0247 , H05K5/03 , H05K5/061 , H05K7/20909 , H05K7/20927 , H01L2924/00
摘要： A power electronics module is provided having one or more power converter semiconductor components. The power electronics module further has a substrate having a first surface to which the one or more components are mounted, and having an opposing second surface from which project a plurality of heat transfer formations for enhancing heat transfer from the substrate. The power electronics module further has a coolant housing which sealingly connects to the substrate to form a void over the heat transfer formations of the second surface. The coolant housing has an inlet for directing a flow of an electrically insulating coolant into the void and an outlet for removing the coolant flow from the void, whereby heat generated during operation of the one or more components is transferred into the coolant flow via the substrate.
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40.发明申请公开(公告)号：US20170298955A1
公开(公告)日：2017-10-19
申请号：US15638822
申请日：2017-06-30
申请人： DRESSER-RAND COMPANY
CPC分类号： F04D29/58 , F04D17/12 , F04D25/0686 , F04D27/0292 , F04D29/058 , F04D29/124 , F04D29/5806 , F04D29/584 , F05D2260/85
摘要： A system and method for rapid pressurization of a motor compartment and cooling system during a shutdown, a surge, and/or other situations in which the suction pressure significantly varies. A motor/compressor arrangement includes a seal gas system fluidly communicating with the motor compartment via a motor pressurization line, with the outlet of the compressor, and with a shaft seal. A motor pressurization valve is coupled to the motor pressurization line and a controller is configured to open the motor pressurization valve at start-up of the motor-compressor to supply seal gas to the motor compartment and to pressurize the motor compartment when a difference between the seal gas supply pressure and the suction pressure is indicative of the seal gas supply pressure being insufficient.
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