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公开(公告)号：US20240271575A1
公开(公告)日：2024-08-15
申请号：US18645585
申请日：2024-04-25
CPC分类号： F02C9/22 , F04D27/001 , F05D2220/323 , F05D2260/81 , F05D2270/301 , F05D2270/304 , F05D2270/306 , F05D2270/71
摘要： A system and a method for configuring at least one variable geometry mechanism (VGM) of an aircraft engine are provided. Pass-off testing data for the aircraft engine is obtained, the pass-off testing data indicative of an actual value of at least one operating parameter of the aircraft engine. Based on the pass-off testing data, at least one trim value to be used to adjust a setting of the at least one VGM to bring the actual value of the at least one operating parameter towards a target value is determined, a running line of the aircraft engine being substantially constant when the actual value of the at least one operating parameter is at the target value. The setting of the at least one VGM is adjusted, during pass-off testing of the aircraft engine, using the at least one trim value.
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公开(公告)号：US20200132086A1
公开(公告)日：2020-04-30
申请号：US16175986
申请日：2018-10-31
发明人： Martin DROLET , Jason NICHOLS
摘要： A compressor diffuser for a gas turbine engine includes a plurality of diffuser passages including a first portion having a radial component, a second portion having an axial component, and a curved portion fluidly connecting the first portion and the second portion. The diffuser passages having a throat located within the first portion thereof, and including a first subset of passages and a second subset of passages. The throats of the first subset of passages have a first throat area that is different than a throat area of the throats of the second subset of passages.
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公开(公告)号：US20230113130A1
公开(公告)日：2023-04-13
申请号：US18082008
申请日：2022-12-15
发明人： Martin DROLET , Frederic FORTIN
摘要： There are described methods and systems for operating an aircraft having two or more engines. One method comprises operating the two or more engines of the aircraft in an asymmetric operating regime, wherein a first of the engines is in an active mode to provide motive power to the aircraft and a second of the engines is in a standby mode to provide substantially no motive power to the aircraft; governing the first engine in the active mode using a first governing logic; and governing the second engine in the standby mode using a second governing logic, the second governing logic based on a target compressor speed and variable geometry mechanism (VGM) settings that are adjusted using trim values dependent on at least one parameter of the second engine in the standby mode.
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公开(公告)号：US20220106915A1
公开(公告)日：2022-04-07
申请号：US17063188
申请日：2020-10-05
IPC分类号： F02C9/54
摘要： There are described a method and system for operating a gas turbine engine. The method comprises governing the engine with a primary governing logic to adjust a fuel flow to the engine and governing the engine with at least one complementary governing logic concurrently to the primary governing logic, the at least one complementary governing logic adjusting a position of at least one variable geometry mechanism (VGM) of the engine to prevent a rotational speed of the engine from operating in one or more restricted speed range.
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5.发明公开公开(公告)号：US20230143026A1
公开(公告)日：2023-05-11
申请号：US17521352
申请日：2021-11-08
发明人： Martin DROLET , Yves CLOUTIER
CPC分类号： F02C9/22 , F02C9/18 , F05D2200/211 , F05D2200/13 , F05D2200/14 , F05D2220/323 , F05D2270/3015 , F05D2270/303 , F05D2270/3061 , F05D2270/335 , F05D2270/71
摘要： The method can include determining a mass flow rate W of working fluid circulating through the compressor stage, determining a control parameter value associated to the geometrical configuration of the variable geometry element based on the determined value of mass flow rate W; and changing the geometrical configuration of the variable geometry element in accordance with the determined control parameter value.
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公开(公告)号：US20210381525A1
公开(公告)日：2021-12-09
申请号：US17407525
申请日：2021-08-20
发明人： Martin DROLET
摘要： There is disclosed a centrifugal compressor including an impeller rotatable about an axis and a diffuser downstream of the impeller. The diffuser has walls delimiting flow passages. Plasma actuators are positioned adjacent the walls and are operatively connectable to a source of electricity. The plasma actuators have a first electrode, a second electrode, and a dielectric layer therebetween. The first electrode is upstream of the second electrode. The first electrode is exposed to the flow passage. The second electrode is shielded from the flow passage by the dielectric layer. The plasma actuators are operable to generate an electric field through the dielectric layer. The plasma actuators are located closer to inlets of the flow passage than to outlets of the flow passages. A method of operating the compressor is disclosed.
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公开(公告)号：US20200248623A1
公开(公告)日：2020-08-06
申请号：US16267575
申请日：2019-02-05
发明人： Martin DROLET
摘要： A system and method for detecting inlet temperature distortion of an engine are described. The method comprises obtaining an outside air temperature from at least one first sensor, obtaining an inlet temperature of the engine from at least one second sensor, determining an inlet temperature distortion based on a difference between the outside air temperature and the inlet temperature, comparing the inlet temperature distortion to a threshold, and issuing an alert when the inlet temperature distortion exceeds the threshold.
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公开(公告)号：US20230050939A1
公开(公告)日：2023-02-16
申请号：US17402352
申请日：2021-08-13
发明人： Martin DROLET , Francis DEMERS
IPC分类号： F02C9/18
摘要： In a method for operating an engine, a request for an increase in thrust generated by the engine is received. In response to receipt of the request, a determination is made as to whether at least one operating condition for heat application-based thrust is met. If so, a heat source is applied to heat bypass air flowing through the bypass duct towards the exhaust nozzle and the increase in thrust is generated from an increased temperature of mixed bypass air and core air at the exhaust nozzle.
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公开(公告)号：US20230026702A1
公开(公告)日：2023-01-26
申请号：US17382922
申请日：2021-07-22
摘要： A system and a method for configuring at least one variable geometry mechanism (VGM) of an aircraft engine are provided. Pass-off testing data for the aircraft engine is obtained, the pass-off testing data indicative of an actual value of at least one operating parameter of the aircraft engine. Based on the pass-off testing data, at least one trim value to be used to adjust a setting of the at least one VGM to bring the actual value of the at least one operating parameter towards a target value is determined, a running line of the aircraft engine being substantially constant when the actual value of the at least one operating parameter is at the target value. The setting of the at least one VGM is adjusted, during pass-off testing of the aircraft engine, using the at least one trim value.
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公开(公告)号：US20220106913A1
公开(公告)日：2022-04-07
申请号：US17061657
申请日：2020-10-02
发明人： Martin DROLET , Frederic FORTIN
摘要： There are described methods and systems for operating an aircraft having two or more engines. One method comprises operating the two or more engines of the aircraft in an asymmetric operating regime, wherein a first of the engines is in an active mode to provide motive power to the aircraft and a second of the engines is in a standby mode to provide substantially no motive power to the aircraft; governing the first engine in the active mode using a first governing logic; and governing the second engine in the standby mode using a second governing logic, the second governing logic based on a target compressor speed and variable geometry mechanism (VGM) settings that are adjusted using trim values dependent on at least one parameter of the second engine in the standby mode.
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