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公开(公告)号：US11663863B2
公开(公告)日：2023-05-30
申请号：US16657695
申请日：2019-10-18
CPC分类号： G07C5/12 , B64D43/00 , G07C5/0816
摘要： The present disclosure provides methods and systems for operating a rotorcraft comprising a plurality of engines configured to provide motive power to the rotorcraft. The rotorcraft is operated in a first flight regime. A target output power range for at least one of the plurality of engines is determined, the target output power range associated with operating the rotorcraft in a second flight regime different from the first flight regime in which at least one first engine of the plurality of engines is operated in an active mode to provide motive power to the rotorcraft and at least one second engine of the plurality of engines is operated in a standby mode to provide substantially no motive power to the rotorcraft. A graphical representation of the target output power range for the second flight regime is produced via a flight display in a cockpit of the rotorcraft.
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公开(公告)号：US11578663B2
公开(公告)日：2023-02-14
申请号：US16565736
申请日：2019-09-10
发明人： Ghislain Plante , Keith Morgan , Stephen Mah , Patrick Valois , Robert Peluso
摘要： A method of providing an engine family includes providing a first engine having a low pressure turbine driving a low pressure compressor at a first speed ratio, and a high pressure turbine driving a high pressure compressor. The method includes providing a second engine by changing the first speed ratio of the first engine to a second speed ratio.
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公开(公告)号：US11920479B2
公开(公告)日：2024-03-05
申请号：US16535256
申请日：2019-08-08
IPC分类号： F01D13/02 , B64C27/12 , B64D27/10 , B64D35/04 , F01D15/12 , F01D17/16 , F02C6/02 , F02C6/20 , F02C7/36 , F02C9/56
CPC分类号： F01D13/02 , B64C27/12 , B64D27/10 , B64D35/04 , F01D15/12 , F01D17/162 , F02C6/02 , F02C6/20 , F02C7/36 , F02C9/56 , F05D2220/329 , F05D2240/12 , F05D2240/60 , F05D2260/4031
摘要： A method of operating a multi-engine system of a rotorcraft includes, during a cruise flight segment of the rotorcraft, controlling a first engine to provide sufficient power and/or rotor speed demands of the cruise flight segment; and controlling a second engine to by providing a fuel flow to the second engine that is between 70% and 99.5% less than a fuel flow provided to the first engine. A turboshaft engine for a multi-engine system configured to drive a common load is also described.
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公开(公告)号：US11408352B2
公开(公告)日：2022-08-09
申请号：US17077310
申请日：2020-10-22
发明人： Keith Morgan , Robert Peluso , Ghislain Plante , Eugene Gekht , Eric Durocher , Jean Dubreuil , Stephen Mah , Philippe Beauchesne-Martel
IPC分类号： F02C7/32 , F02C3/14 , F02C6/20 , F02C3/04 , F02C3/067 , F02C3/113 , F02C7/36 , F01D1/26 , F04D25/02
摘要： A gas turbine engine has a first spool having a low pressure compressor section in fluid communication with an air inlet, the low pressure compressor section including a first plurality of variable guide vanes therein, and a low pressure turbine section drivingly engaged to the low pressure compressor section. A second spool has a high pressure compressor section in fluid communication with the low pressure compressor section to receive pressurized air therefrom, the high pressure compressor section including a second plurality of variable guide vanes at an entry thereof, and a high pressure turbine section drivingly engaged to the high pressure compressor section, the high pressure turbine section disposed upstream of the low pressure turbine section and in fluid communication therewith. An output drive shaft drivingly engages the low pressure turbine section and is adapted to drivingly engage a rotatable load of the gas turbine engine.
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公开(公告)号：US11643965B2
公开(公告)日：2023-05-09
申请号：US16671070
申请日：2019-10-31
CPC分类号： F02C6/20 , B64D31/06 , F02C6/02 , F02C9/00 , F05D2220/323 , F05D2220/329 , F05D2270/11 , F05D2270/70
摘要： Methods and systems for operating a rotorcraft comprising a plurality of engines are provided. A request to enter into an asymmetric operating regime (AOR), in which at least one active engine of the plurality of engines is operated in an active mode to provide motive power to the rotorcraft and at least one standby engine of the plurality of engines is operated in a standby mode to provide substantially no motive power, is obtained. Engine usage data for the plurality of engines, including at least one first engine and at least one second engine, is determined. Based on the engine usage data, one of the at least one first and second engines is operated as the at least one active engine for the AOR, and the other one of the at least one first and second engines is operated as the at least one standby engine for the AOR.
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公开(公告)号：US11629665B2
公开(公告)日：2023-04-18
申请号：US16565722
申请日：2019-09-10
发明人： Ghislain Plante , Keith Morgan , Stephen Mah , Patrick Valois , Robert Peluso
摘要： An aircraft engine has a high pressure spool including a high pressure turbine drivingly connected to a high pressure compressor. A low pressure spool including a low pressure compressor is fluidly connected to the high pressure compressor. A low pressure turbine is drivingly connected to the low pressure compressor to drive the low pressure compressor. A load is drivingly connected to the low pressure turbine, the load consisting of one of a propeller and a helicopter rotor. A method of creating classes of an aircraft engine from an engine platform is disclosed.
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