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公开(公告)号：US11814989B2
公开(公告)日：2023-11-14
申请号：US17514672
申请日：2021-10-29
发明人： Eric Durocher
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F05D2220/32 , F05D2240/12
摘要： An apparatus is provided for a gas turbine engine. This gas turbine engine apparatus includes a first platform, a second platform, a plurality of vanes and a plurality of beams. The first platform extends axially along and circumferentially about an axis. The second platform extends axially along and circumferentially about the axis. The vanes are arranged circumferentially about the axis. Each of the vanes extends radially across a gas path between the first platform and the second platform. The vanes include a first vane movably connected to the first platform. The beams are arranged circumferentially about the axis. The beams are fixedly connected to the first platform and the second platform. The beams include a first beam extending radially through the first vane.
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公开(公告)号：US11480475B2
公开(公告)日：2022-10-25
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：US11041443B2
公开(公告)日：2021-06-22
申请号：US16583896
申请日：2019-09-26
发明人： Eric Durocher , Keith Morgan , Lazar Mitrovic , Jean Dubreuil , Martin Poulin
摘要： A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.
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公开(公告)号：US10760527B2
公开(公告)日：2020-09-01
申请号：US15019341
申请日：2016-02-09
发明人： Guy Lefebvre , Nicolas Grivas , Richard Bouchard , Denis Leclair , Eric Durocher
摘要： An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.
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公开(公告)号：US09284915B2
公开(公告)日：2016-03-15
申请号：US14263098
申请日：2014-04-28
发明人： Guy Lefebvre , Nicolas Grivas , Richard Bouchard , Denis Leclair , Eric Durocher
CPC分类号： F02K1/386 , F01D9/04 , F02K1/48 , F02K1/80 , F05D2220/32 , F05D2230/642 , F05D2240/10 , F05D2240/127 , Y02T50/671
摘要： An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.
摘要翻译： 用于燃气涡轮发动机的排气混合器包括具有适于紧固到发动机壳体的上游端的环形壁和形成多个内部和外部混合器凸角的下游端。 支撑构件互连至少多个内裂片，并且包括从内裂片径向向内定位的周向延伸的加强环，以及一系列周向间隔开的从内裂纹到加强环径向延伸的混合器支柱。 混合器支柱具有至少等于限定在内部叶片和排气锥体之间的主气体通道的宽度的径向长度，使得混合器支柱完全延伸穿过主气体路径。 加强环仅被固定到混合器支柱上，以便相对于排气锥体浮动并允许它们之间的相对运动。
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公开(公告)号：US08876463B2
公开(公告)日：2014-11-04
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：US12098644B2
公开(公告)日：2024-09-24
申请号：US18056032
申请日：2022-11-16
发明人： Keith Morgan , Eric Durocher
IPC分类号： F02C3/08 , B64C27/12 , B64D27/10 , B64D35/04 , F01D13/02 , 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 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：US11732645B2
公开(公告)日：2023-08-22
申请号：US17367774
申请日：2021-07-06
发明人： Eric Durocher
CPC分类号： F02C6/08 , F01D9/06 , F01D17/145 , F05D2220/323 , F05D2250/231 , F05D2260/606
摘要： A gas turbine engine comprising: a duct extending about an axis, the duct including an outer-duct wall having an interior-duct surface circumscribing an interior of the duct and an exterior-duct surface radially outward of the interior-duct surface relative to the axis, the outer-duct wall defining an offtake opening extending from the interior-duct surface to the exterior-duct surface, the offtake opening in fluid communication between an offtake location inside the duct and outside the duct, and a bleed air offtake assembly including: an air line in fluid communication with inside the duct via the offtake opening, the air line having a first-line end defining a line inlet proximate to the outer-duct wall and a second-line end spaced from the first-line end; a valve located outside the duct and fluidly connected to the air line via the second-line end, and a conduit having a conduit inlet in fluid communication with inside the air line at a resonance location between the first-line end and the second-line end upstream of the valve, and a conduit outlet in fluid communication with inside the duct at a relief location spaced from the offtake location.
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公开(公告)号：US11635024B2
公开(公告)日：2023-04-25
申请号：US16991224
申请日：2020-08-12
发明人： Laurent Letourneau , Keith Morgan , John Wilson , Paul Weaver , Eric Durocher
摘要： A turboprop gas turbine engine mountable to an aircraft has an engine core and a gearbox driving a propeller, the engine core and the gearbox being enclosed within a nacelle. The propeller is located rearward of the gearbox and the engine core relative to a direction of travel of the aircraft. An air intake is disposed within the nacelle and formed to direct ambient air into the engine core. The air intake includes an air inlet duct, having a forward-facing intake inlet receiving the ambient air, with an upstream section and a downstream section. The upstream section is in fluid communication with the intake inlet and extends downstream from the intake inlet. The downstream section fluidly connects to and directs air from the upstream section into the engine air inlet. A second air outlet duct is located within the nacelle and directs air into an air-cooled-oil-cooler (ACOC).
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公开(公告)号：US11555453B2
公开(公告)日：2023-01-17
申请号：US17368317
申请日：2021-07-06
发明人： Keith Morgan , Robert Peluso , Ghislain Plante , Eugene Gekht , Eric Durocher , Jean Dubreuil
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 disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.
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