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公开(公告)号：US20210003458A1
公开(公告)日：2021-01-07
申请号：US16502341
申请日：2019-07-03
发明人： Eric DUROCHER , Scott SMITH , Guy BOUCHARD
摘要： A system and method for measuring average temperature of gas in an axial cross-section of a gas turbine engine gas path, involving diverting gas samples from different positions in the axial cross-section to a gas mixing chamber and measuring a temperature of the resulting mixed gas.
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公开(公告)号：US20190120170A1
公开(公告)日：2019-04-25
申请号：US16219189
申请日：2018-12-13
发明人： Eric DUROCHER , Guy LEFEBVRE
CPC分类号： F02K1/48 , B21D53/92 , Y10T29/49323
摘要： A mixer of a bypass turbine aeroengine according to one embodiment, includes circumferential inner and outer flow surfaces in a wavy configuration to form a plurality of lobes of the mixer. The mixer has an upstream end portion of sheet metal with a first thickness and a downstream end portion of sheet metal with a second thickness less than the first thickness.
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3.发明申请公开(公告)号：US20170327241A1
公开(公告)日：2017-11-16
申请号：US15412451
申请日：2017-01-23
发明人： Lazar MITROVIC , Eric DUROCHER , Keith MORGAN
IPC分类号： B64D35/08 , F02C7/262 , B64D27/10 , B64D31/06 , F02C7/275 , B64C27/12 , F02C7/22 , F02C6/02 , F16D48/02 , F02C7/36
摘要： A method of operating a twin engine helicopter power plant, the power plant comprising: two turboshaft engines each having an engine shaft with a turbine at a distal end and a one-way clutch at a proximal end; a gear box having an input driven by the one way clutch of each engine and an output driving a helicopter rotor; a bypass clutch disposed between the proximal end of each engine shaft and the input of the gear box; and power plant management system controls for activating the bypass clutch; the method comprising: detecting when a rotary speed of an associated engine shaft is less than a rotary speed of the gear box input; activating the bypass clutch to drive the associated engine shaft using the rotation of the gear box input; and starting an associated engine by injecting fuel when the bypass clutch is activated.
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公开(公告)号：US20140133962A1
公开(公告)日：2014-05-15
申请号：US13942876
申请日：2013-07-16
发明人： Eric DUROCHER , Nicolas GRIVAS
CPC分类号： F01D25/14 , F01D5/18 , F01D11/005 , F01D25/28 , F05D2260/20
摘要： A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil.
摘要翻译： 燃气涡轮发动机具有设置在涡轮转子组件之间的中间涡轮机架。 中间涡轮机框架包括径向延伸穿过环形气体通道导管的中空翼型件。 翼型件各自包括双壁前缘结构，以限定与在翼型内的剩余空间中限定的后室分离的前室。
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公开(公告)号：US20230193774A1
公开(公告)日：2023-06-22
申请号：US17644630
申请日：2021-12-16
发明人： Ian MACFARLANE , Eric DUROCHER , Guy LEFEBVRE
CPC分类号： F01D11/02 , F02C7/28 , F05D2220/323 , F05D2240/55
摘要： A labyrinth seal assembly comprising: an outer seal having a radially inner cavity surface, and an axial cavity surface inward of the radially inner cavity surface; a floating seal received by the outer seal so as to be movable in a radial direction relative to the outer seal, the floating seal having a radially outer seal surface spaced inwardly from the radially inner cavity surface, a radially inner surface inward of the radially outer seal surface, and an axial seal surface bearing against the axial cavity surface; and an inner seal received by the floating seal, the inner seal having a radially outer surface spaced inwardly from the radially inner surface, a first one of the radially outer surface and the radially inner surface defining one tooth projecting toward a second one of the radially outer surface and the radially inner surface to inward of the axial seal surface.
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公开(公告)号：US20230075494A1
公开(公告)日：2023-03-09
申请号：US18056032
申请日：2022-11-16
发明人： Keith MORGAN , Eric DUROCHER
IPC分类号： F01D13/02 , F02C9/56 , B64D35/04 , F01D15/12 , B64C27/12 , B64D27/10 , F01D17/16 , F02C6/02 , F02C6/20 , F02C7/36
摘要： A turboshaft engine for a rotorcraft includes a first spool and an independently rotatable second spool. The first spool includes a low pressure compressor, a first set of variable guide vanes disposed at an entry of the low pressure compressor, and a low pressure turbine drivingly engaged to the low pressure compressor. The second spool includes a high pressure compressor, a second set of variable guide vanes disposed at an entry of the high pressure compressor, the second set of variable guide vanes independently operable relative to the first set of variable guide vanes, and a high pressure turbine drivingly engaged to the high pressure compressor. One or both of the low pressure compressor and the high pressure compressor includes a mixed flow rotor.
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公开(公告)号：US20200049025A1
公开(公告)日：2020-02-13
申请号：US16535256
申请日：2019-08-08
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：US20140075919A1
公开(公告)日：2014-03-20
申请号：US13621467
申请日：2012-09-17
发明人： Eric DUROCHER , Guy LEFEBVRE
CPC分类号： F02K1/48 , B21D53/92 , Y10T29/49323
摘要： A mixer of a bypass turbine aeroengine according to one embodiment, includes circumferential inner and outer flow surfaces in a wavy configuration to form a plurality of lobes of the mixer. The mixer has an upstream end portion of sheet metal with a first thickness and a downstream end portion of sheet metal with a second thickness less than the first thickness.
摘要翻译： 根据一个实施例的旁路涡轮机航空发动机的混合器包括波浪形结构中的周向内部和外部流动表面，以形成混合器的多个叶片。 混合器具有第一厚度的第一厚度的金属板的上游端部分和具有小于第一厚度的第二厚度的金属板的下游端部分。
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公开(公告)号：US20210270183A1
公开(公告)日：2021-09-02
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
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：US20180135522A1
公开(公告)日：2018-05-17
申请号：US15351803
申请日：2016-11-15
摘要： A gas turbine engine has an in-line mounted accessory gear box (AGB) and an accessory drivingly connected to the AGB, the accessory being oriented transversally to the engine centerline.
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