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公开(公告)号：US12044185B2
公开(公告)日：2024-07-23
申请号：US18206851
申请日：2023-06-07
CPC分类号： F02C9/52 , F02C9/28 , F02C9/54 , F05D2260/606 , F05D2270/05
摘要： A control device includes a suction amount controller and a bleed flow controller. When an actual output is in a second output range from a second output to a third output less than the second output, the suction amount controller controls a suction amount so that the suction amount becomes constant even if the actual output decreases. The bleed flow controller controls a bleed flow so that the bleed flow gradually increases as the actual output decreases.
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公开(公告)号：US20240093649A1
公开(公告)日：2024-03-21
申请号：US18273432
申请日：2022-03-23
发明人： Akitomo TSUKAHARA
CPC分类号： F02C9/54 , F01D15/10 , F01D17/02 , F02C7/042 , F05D2220/32 , F05D2220/76 , F05D2240/12 , F05D2270/053 , F05D2270/06
摘要： A gas turbine system and control method for the gas turbine system that includes a gas turbine having a compressor for producing compressed air, a combustor for burning fuel with the compressed air, a turbine driven by a combustion gas generated by burning the fuel in the combustor, and an inlet guide vane for adjusting an intake air amount of the compressor; an inlet guide vane control device for controlling an opening degree of the inlet guide vane; and a motor generator drivable by the turbine and capable of providing rotational power to the gas turbine by electric power supplied from outside the gas turbine. The inlet guide vane control device controls the opening degree of the inlet guide vane to be an opening degree greater than a minimum opening degree which is a minimum value of the opening degree of the inlet guide vane in a normal operation mode.
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公开(公告)号：US11898449B2
公开(公告)日：2024-02-13
申请号：US17092525
申请日：2020-11-09
申请人： ABB Schweiz AG
发明人： Camilo Lopez , Mark Foltz , Steve Miller
IPC分类号： F01C20/28 , G01P21/02 , G01R31/28 , F01D17/06 , F02C9/28 , F01D21/02 , H02J3/38 , H02J3/40 , F01K13/00 , F01K13/02 , F16K37/00 , F02C7/232 , F02C9/26 , F02C9/52 , F02C9/54 , F01D17/14 , F01D17/26
CPC分类号： F01C20/28 , F01D17/06 , F01D17/145 , F01D17/26 , F01D21/02 , F01K13/003 , F01K13/02 , F02C7/232 , F02C9/263 , F02C9/28 , F02C9/52 , F02C9/54 , F16K37/0041 , F16K37/0083 , G01P21/02 , G01R31/2829 , H02J3/381 , H02J3/40 , F05D2220/31 , F05D2260/80 , F05D2270/02 , F05D2270/021 , F05D2270/80
摘要： A turbine control system is provided for decreasing the response time between readings of the speed of the turbine and changing a valve position in response thereto. The speed control system includes a speed probe that detects the speed of the turbine and a turbine valve that controls the flow of fluid or gas from or to the turbine. A controller receives a speed signal from the speed probe and sends valve position commands to the turbine valve. The controller also sends support functions to the turbine valve. The controller sends the valve position commands at a faster rate than the support functions.
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公开(公告)号：US11746672B2
公开(公告)日：2023-09-05
申请号：US17601342
申请日：2020-04-03
CPC分类号： F01D17/14 , F02K1/15 , F02K1/76 , F01D7/00 , F01D7/02 , F01D17/162 , F02C9/22 , F02C9/54 , F05D2220/32 , F05D2240/12 , F05D2270/30
摘要： The present invention concerns a method for monitoring an actuating system of a movable component, in particular a movable component of a turbomachine such as a nozzle or a blade, the actuating system comprising a control device configured to deliver a position instruction to a first cylinder and a second cylinder, each cylinder being configured to deliver a position feedback measurement in response to the position instruction, the method being implemented in a monitoring system and comprising, —a first monitoring mode in which the deviations between the position feedback measurements of the two cylinders are detected; —a second monitoring mode in which the deviations between the position feedback measurements of the two cylinders are not detected; method in which the second mode is selected when at least one of the two position feedback measurements is in a transient phase.
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公开(公告)号：US11585354B2
公开(公告)日：2023-02-21
申请号：US17840685
申请日：2022-06-15
IPC分类号： F04D29/56 , F01D17/16 , F01D9/02 , F02C7/20 , F02C9/54 , F02K3/06 , F04D29/32 , F04D29/52 , F04D29/54
摘要： An un-ducted turbofan engine defining a radial direction and an axial direction that includes a core engine, a fan, a plurality of variable outlet guide vanes, and a pitch change mechanism. Each of the plurality of variable outlet guide vanes are attached in a rotatable manner to the core engine of the un-ducted turbofan engine. The pitch change mechanism is positioned radially between the engine air flowpath and the plurality of variable outlet guide vanes and coupled to at least one variable outlet guide vane of the plurality of variable outlet guide vanes for changing a pitch of the at least one variable outlet guide vane.
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公开(公告)号：US11555458B2
公开(公告)日：2023-01-17
申请号：US17163981
申请日：2021-02-01
发明人： Benjamin Roy , Bryan Fishbein , Timothy Arulsuthan
摘要： Methods and systems for detecting and responding to an engine disturbance are described. The method comprises monitoring a rate of change of a combustor pressure of an engine, detecting an engine disturbance when the rate of change of the combustor pressure falls below an event detection threshold, initiating an engine recovery sequence in response to detecting the engine disturbance, confirming a surge event when the rate of change of the combustor pressure increases above a surge confirmation threshold within a flameout confirmation time period after having crossed the event detection threshold, applying a surge recovery sequence in response to confirming the surge event, confirming a flameout event when the flameout confirmation time period expires and the rate of change of the combustor pressure remains below the surge confirmation threshold after having crossed the event detection threshold, and applying a flameout recovery sequence in response to confirming the flameout event.
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公开(公告)号：US11378017B2
公开(公告)日：2022-07-05
申请号：US16448214
申请日：2019-06-21
申请人： ROLLS-ROYCE plc
发明人： Rory D Stieger , Conor Hickey
摘要： A turbofan engine has an engine core including in flow series a compressor, a combustor and a turbine. The engine further has a fan located upstream of the engine core, has a supersonic intake for slowing down incoming air to subsonic velocities at an inlet to the fan formed by the intake, has a bypass duct surrounding the engine core, wherein the fan generates a core airflow to the engine core and a bypass airflow through the bypass duct, and has a mixer for mixing an exhaust gas flow exiting the engine core and bypass airflow exiting bypass duct. The engine further has a thrust nozzle rearwards of the mixer for discharging mixed flows, the thrust nozzle having a variable area throat. The engine further has a controller controlling the thrust produced by the engine over a range of flight operations including on-the-ground subsonic take-off and subsequent off-the-ground subsonic climb.
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公开(公告)号：US11339721B2
公开(公告)日：2022-05-24
申请号：US16190461
申请日：2018-11-14
发明人： Harold Riley , Michael Dwyer
摘要： A system and method for supplying compressed air from an auxiliary power unit to a main engine starter motor. The inlet guide vanes are controlled using either first or second inlet guide vane control logic and the surge control valve is controlled using either first or second surge control valve control logic. When the first inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand signal, when the second inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand schedule, when the first surge control valve logic is used, the surge control valve can be commanded to repeatedly move to only a fully-closed position and a fully-open position, and when the second surge control valve logic is used, the surge control valve can be commanded to the fully-closed position only when maximum flow is commanded.
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公开(公告)号：US11274610B2
公开(公告)日：2022-03-15
申请号：US17045809
申请日：2019-03-29
发明人： Jadeed Beita , Andrew Dawson
摘要： A method of controlling a combustion system of a gas turbine engine which has a combustor with a primary combustion zone, of which a condition in the primary combustion zone is defined by a primary zone control parameter. The method includes controlling the primary zone control parameter to be substantially constant value over a range of values of compressor inlet air temperature.
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公开(公告)号：US11260983B2
公开(公告)日：2022-03-01
申请号：US16552433
申请日：2019-08-27
申请人： Rolls-Royce plc
摘要： This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor.
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