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公开(公告)号：US11859554B2
公开(公告)日：2024-01-02
申请号：US17388308
申请日：2021-07-29
CPC分类号： F02C7/26 , B64D31/00 , F02C6/20 , F02C9/18 , F05D2220/323 , F05D2220/74 , F05D2240/35 , F05D2260/85
摘要： A method of operating a multi-engine system of an aircraft having first and second engines includes accumulating compressed air in a pressure vessel external to the engines, and operating the first and second engines asymmetrically, by controlling the first engine to operate in an active operating condition providing sufficient power and/or rotor speed for demands of the aircraft, and controlling the second engine to operate in a standby operating condition wherein the second engine produces less power output than the first engine. In response to a power demand request, the second engine is accelerated out of the standby operating condition by introducing therein compressed air from the pressure vessel at a location upstream of a combustor of the second engine.
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公开(公告)号：US11535386B2
公开(公告)日：2022-12-27
申请号：US16671551
申请日：2019-11-01
IPC分类号： G01C23/00 , B64D15/16 , B64C27/00 , B64D15/20 , F02C6/02 , F02C6/20 , F02C9/22 , F02C9/26 , B64C27/06 , B64D27/10 , B64D31/14
摘要： There is provided a system and a method for operating a multi-engine rotorcraft. When the rotorcraft is cruising in an asymmetric operating regime (AOR) at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of a power level of the at least one second engine is increased and at least one variable geometry mechanism of the at least one second engine is moved to shed any ice accumulation on the at least one second engine.
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公开(公告)号：US10822104B2
公开(公告)日：2020-11-03
申请号：US16110699
申请日：2018-08-23
摘要： Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A power level difference between a requested engine power level and a current engine power level is determined at a computing device. The power level difference is compared to a predetermined power threshold at the computing device. When the power level difference exceeds the predetermined power threshold, a position control signal for changing a position of the variable geometry mechanism is generated and output at the computing device, the position control signal generated based on a requisite bias level, the requisite bias level being based on the power level difference.
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公开(公告)号：US10808624B2
公开(公告)日：2020-10-20
申请号：US15428572
申请日：2017-02-09
IPC分类号： F02C7/32 , B64D27/10 , F02C3/107 , F02C7/36 , F01D15/10 , F01D15/12 , F04D29/32 , F04D29/053 , F02C3/10 , F02C6/20 , F01D15/00 , F02C3/14
摘要： A method and a turbine rotor system for reducing over-speed potential of a turbine of a gas turbine engine involve mechanically connecting the turbine to at least two mechanical loads via first and second mechanical drives extending in opposite directions from the turbine.
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公开(公告)号：US20190063331A1
公开(公告)日：2019-02-28
申请号：US16033142
申请日：2018-07-11
摘要： Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A pressure ratio between a first pressure at an inlet of the engine and a predetermined reference pressure is determined. An output power for the engine is determined. The output power is adjusted based at least in part on the pressure ratio to obtain a corrected output power. A position control signal for a variable geometry mechanism of the engine is generated based on the corrected output power and the pressure ratio. The position control signal is output to a controller of the engine to control the variable geometry mechanism.
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公开(公告)号：US11939914B2
公开(公告)日：2024-03-26
申请号：US17540576
申请日：2021-12-02
CPC分类号： F02C6/02 , B64D27/10 , B64D31/00 , F02C6/20 , F02C9/42 , F05D2220/329 , F05D2260/96 , F05D2270/02
摘要： There is described a method of operating a multi-engine system of an helicopter. The multi-engine system has a first turboshaft engine having a first shaft, a second turboshaft engine having a second shaft, a gearbox having a clutch system, and a range of rotation speeds defined as a placarded zone. The method generally has rotating the first shaft at a flight rotation speed when clutched and rotating the second shaft at a first idle rotation speed when unclutched, the first idle rotation speed above the placarded zone; decreasing a rotation speed of the first shaft from the flight rotation speed to a given rotation speed within the placarded zone; decreasing a rotation speed of the second shaft to the given rotation speed; clutching the second shaft; and decreasing the rotation speeds of the first and second shafts to a second idle rotation speed below the placarded zone.
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公开(公告)号：US11867129B2
公开(公告)日：2024-01-09
申请号：US18119017
申请日：2023-03-08
CPC分类号： F02C9/00 , B64D31/04 , B64D31/12 , F05D2220/323 , F05D2270/02 , F05D2270/13
摘要： In an asymmetric operating regime, a first engine is operating in an active mode to provide motive power to an aircraft while a second engine is operating in a standby mode and de-clutched from a gearbox of the aircraft. In response to an emergency exit request, the second engine's speed is increased, at a maximum permissible rate, to a re-clutching speed while increasing the first engine's power output at a maximum permissible rate. When the re-clutching speed is reached, the second engine's power output is increased at a maximum permissible rate. In response to a normal exit request, the second engine's speed is increased to the re-clutching speed at a rate lower than the maximum permissible rate. When the re-clutching speed is reached, the second engine's power output is increased at a rate lower than the maximum permissible rate.
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公开(公告)号：US20230323790A1
公开(公告)日：2023-10-12
申请号：US17719037
申请日：2022-04-12
CPC分类号： F01D17/162 , F01D17/02 , F05D2270/821 , F05D2270/802 , G01B21/042
摘要： A method for calibrating a position sensor of a variable vane assembly for a gas turbine engine includes positioning an actuator member in at least one predetermined position, determining a first measured position of the actuator member in the at least one predetermined position with a first channel of a position sensor, determining a second measured position of the actuator member in the at least one predetermined position with a second channel of a position sensor, determining a measured position difference between the first measured position and the second measured position, and calibrating the second channel of the position sensor by adjusting the second measured position by the measured position difference to determine a second calibrated position.
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公开(公告)号：US11713723B2
公开(公告)日：2023-08-01
申请号：US16425488
申请日：2019-05-29
CPC分类号： F02C9/28 , F02C7/222 , F05D2220/32 , F05D2270/3032
摘要： Systems and methods for operating an engine are described herein. The engine is operated at low power by supplying fuel to a combustor through a first set of fuel nozzles of at least one first manifold and without supplying fuel to the combustor through a second set of fuel nozzles of at least one second manifold. An amount of fuel to at least in part fill the at least one second manifold to impede fuel coking of the second set of fuel nozzles is determined. The amount of fuel is periodically supplied to the at least one second manifold.
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公开(公告)号：US11326525B2
公开(公告)日：2022-05-10
申请号：US16599336
申请日：2019-10-11
摘要： A method of monitoring bleed air provided from a first engine to a second engine of a multi-engine aircraft includes operating the first engine in a powered mode to provide motive power to the multi-engine aircraft; and when the first engine is in the powered mode: actuating an air valve to open an air flow path from a compressor section of the first engine to a plurality of parts of the second engine, after the step of actuating the air valve, determining a change in a temperature in a main gas path of the first engine at a location in the main gas path at or downstream of a combustor of the first engine, and in response to determining that the change is below a threshold, executing an action with respect to the first engine, the air valve, and/or the second engine.
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