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公开(公告)号：US11965459B2
公开(公告)日：2024-04-23
申请号：US17723012
申请日：2022-04-18
发明人： Hien Duong , Jason Nichols
CPC分类号： F02C7/042 , F02C7/052 , F05D2260/607
摘要： An air intake plenum for a gas turbine engine is provided that includes an axial centerline, first and second gas path surfaces, and a plurality of struts. The gas path surfaces are spaced apart from one another and define at least a portion of a plenum interior. The struts extend lengthwise between the gas path surfaces. Each strut has a cross-section geometry. The cross-section geometry has a center, and major and minor axes. The struts are circumferentially spaced apart from one another within the plenum. Each strut is oriented at a clocking angle theta. The clocking angle theta for each respective strut is disposed between the major axis of that strut and a line that intersects the cross-section geometry center of that strut and the axial centerline. At least one strut of the plurality of struts is oriented at a clocking angle theta that is greater than zero.
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公开(公告)号：US11421702B2
公开(公告)日：2022-08-23
申请号：US16546781
申请日：2019-08-21
发明人： Jason Nichols
摘要： An impeller for a centrifugal compressor, the impeller comprising: a hub defining a rotation axis about which the impeller is rotatable; and a vane extending from the hub, the vane having a leading edge, a trailing edge, and a chord defined therebetween, a pressure side of the vane and a suction side of the vane opposite the pressure side, a vane thickness defined transversely between the pressure side and the suction side, the vane thickness reducing over at least a downstream 40% of the chord, the vane thickness having a trailing edge thickness value at the trailing edge of between 40% and 80% of a maximum thickness value of the vane thickness.
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公开(公告)号：US11143201B2
公开(公告)日：2021-10-12
申请号：US16354292
申请日：2019-03-15
发明人： Hien Duong , Jason Nichols
IPC分类号： F04D29/44
摘要： A gas turbine engine for an aircraft having a centrifugal compressor including an impeller with impeller blades extending from a hub, the impeller mounted for rotation about a central longitudinal axis within an outer shroud. A main flow passage wall is located on a shroud side near the impeller exit, the main flow passage wall separating a cavity disposed on the shroud side from the main flow passage. One or more apertures are defined through the main flow passage wall and extending along a respective aperture axis between the cavity and the main flow passage. The apertures have a main flow passage side opening located radially outward from the impeller exit. The aperture axis is disposed at a radial angle relative to the central longitudinal axis.
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公开(公告)号：US20230332540A1
公开(公告)日：2023-10-19
申请号：US17723012
申请日：2022-04-18
发明人： Hien Duong , Jason Nichols
CPC分类号： F02C7/042 , F02C7/052 , F05D2260/607
摘要： An air intake plenum for a gas turbine engine is provided that includes an axial centerline, first and second gas path surfaces, and a plurality of struts. The gas path surfaces are spaced apart from one another and define at least a portion of a plenum interior. The struts extend lengthwise between the gas path surfaces. Each strut has a cross-section geometry. The cross-section geometry has a center, and major and minor axes. The struts are circumferentially spaced apart from one another within the plenum. Each strut is oriented at a clocking angle theta. The clocking angle theta for each respective strut is disposed between the major axis of that strut and a line that intersects the cross-section geometry center of that strut and the axial centerline. At least one strut of the plurality of struts is oriented at a clocking angle theta that is greater than zero.
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公开(公告)号：US20230193819A1
公开(公告)日：2023-06-22
申请号：US17967501
申请日：2022-10-17
发明人： Jason Nichols , Ryan Perera
CPC分类号： F02C6/06 , F04D29/284 , F04D29/441 , F02K3/00 , F02C7/32 , F05D2250/71 , F05D2220/32 , F05D2250/52
摘要： A diffuser pipe has a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a generally radial direction from an inlet of the tubular body, a second portion extending in a generally axial direction and terminating at a pipe outlet, and a bend portion fluidly linking the first portion and the second portion. The tubular body has a length defined between the inlet and the pipe outlet. The tubular body has cross-sectional profiles defined in a plane normal to the pipe center axis. An area of the cross-sectional profile at the pipe outlet is at least 20% greater than an area of the cross-sectional profile at a point upstream from the pipe outlet a distance corresponding to 10% of the length of the tubular body.
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公开(公告)号：US11136993B2
公开(公告)日：2021-10-05
申请号：US16374046
申请日：2019-04-03
发明人： Hien Duong , Peter Townsend , Jason Nichols
IPC分类号： F04D29/44
摘要： A compressor diffuser for a gas turbine engine is described which includes diffuser pipes having a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a generally radial direction, a second portion extending in a generally axial direction and terminating at a pipe outlet, and a bend portion fluidly linking the first portion and the second portion. A first curved side wall of the tubular body along the second portion is shorter than a second curved side wall of the tubular body along the second portion. The second portion of the tubular body has a cross-sectional profile defined in a plane normal to the pipe center axis. The first curved side wall of the cross-sectional profile has a smaller radius than a radius of the second curved side wall of the cross-sectional profile.
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公开(公告)号：US09932892B2
公开(公告)日：2018-04-03
申请号：US14806880
申请日：2015-07-23
发明人： Jean Thomassin , Sebastien Bolduc , Bruno Villeneuve , Stephane Berube , Mike Fontaine , David Gagnon-Martin , Jade Bilodeau , Andre Julien , Pierre-Yves Legare , Jason Nichols
IPC分类号： F02B53/14 , F02C3/04 , F02C6/12 , F02C7/047 , F02C7/052 , F02C7/055 , F02C7/14 , F02C7/36 , F01C11/00 , F02B29/04 , F02B33/40 , F02B39/04 , F02B41/10 , F02C3/107 , F02C6/00 , F02C6/20 , F01C21/18 , F02M31/04 , F02M31/10 , F01C1/22 , F02B53/00
CPC分类号： F02B53/14 , F01C1/22 , F01C11/008 , F01C21/18 , F02B29/0418 , F02B33/40 , F02B39/04 , F02B41/10 , F02B2053/005 , F02C3/04 , F02C3/107 , F02C6/00 , F02C6/12 , F02C6/20 , F02C7/047 , F02C7/052 , F02C7/055 , F02C7/14 , F02C7/36 , F02M31/042 , F02M31/10 , F02M31/107 , F05D2250/312 , F05D2260/40311 , F05D2260/98 , Y02T10/126 , Y02T10/146 , Y02T10/163 , Y02T10/17 , Y02T50/675
摘要： A compound engine assembly having an engine core including at least one internal combustion engine in driving engagement with an engine shaft, a compressor having an outlet in fluid communication with an inlet of the engine core and including at least one rotor rotatable about an axis coaxial with the engine shaft, the engine shaft in driving engagement with the compressor rotor, and a turbine section having an inlet in fluid communication with an outlet of the engine core and including at least one rotor engaged on a rotatable turbine shaft, the turbine shaft configured to compound power with the engine shaft. The turbine and engine shafts are parallel to and radially offset from one another, and the turbine shaft and the axis of the compressor rotor are parallel to and radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.
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公开(公告)号：US09732762B2
公开(公告)日：2017-08-15
申请号：US14469961
申请日：2014-08-27
发明人： Hien Duong , Jason Nichols
CPC分类号： F04D29/384 , F01D5/141 , F01D5/145 , F04D19/00 , F04D19/02 , F04D29/324 , F05D2240/303 , F05D2270/17
摘要： A compressor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip of the airfoil. A leading edge sweep angle is defined relative to a tangent to the airfoil and flow velocity vector at a point on the leading edge. A leading edge dihedral angle is defined relative to the tangent to the airfoil and a vertical at the point on the leading edge. A ratio of the leading edge sweep angle to the leading edge dihedral angle being smaller than 1. A method of forming such airfoil is also presented.
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公开(公告)号：US20140286746A1
公开(公告)日：2014-09-25
申请号：US13783773
申请日：2013-03-04
发明人： Jason Nichols , Peter Townsend , Hien Duong , Vijay Kandasamy
CPC分类号： F02C9/18 , F01D5/145 , F02C3/04 , F04D27/023 , F04D29/526 , F04D29/682 , Y02T50/671
摘要： A gas turbine engine compressor includes a rotor defining a central axis of rotation and a plurality of blades which project into an annular compressor gas flow passage, and a shroud circumferentially surrounding the rotor and having a radially inner surface adjacent to the blade tips. Bleed holes extend through the shroud adjacent the blade tips, each of the bleed holes having an inlet end disposed in the shroud radially inner surface and an outlet end disposed in a shroud radially outer surface. Bleed air removed from the annular gas flow passage flows through the bleed holes from the inlet to the outlet ends. The outlet end of each bleed hole is located circumferentially upstream of the inlet end relative to a direction of rotational flow in the annular gas flow passage driven by a direction of rotation of the rotor.
摘要翻译： 燃气涡轮发动机压缩机包括限定中心旋转轴线的转子和突出到环形压缩机气体流动通道中的多个叶片，以及周向围绕转子并具有与叶片尖端相邻的径向内表面的护罩。 排泄孔延伸穿过邻近叶片尖端的护罩，每个排放孔具有设置在护罩径向内表面中的入口端和设置在护罩径向外表面中的出口端。 从环形气体流动通道移除的排出空气从入口流到出口端。 每个排放孔的出口端相对于由转子的旋转方向驱动的环形气体流动通道中的旋转流动方向位于入口端的周向上方。
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公开(公告)号：US20240271563A1
公开(公告)日：2024-08-15
申请号：US18642138
申请日：2024-04-22
发明人： Hien Duong , Jason Nichols
CPC分类号： F02C7/042 , F02C7/052 , F05D2260/607
摘要： An air intake plenum for a gas turbine engine is provided that includes an axial centerline, first and second gas path surfaces, and a plurality of struts. The gas path surfaces are spaced apart from one another and define at least a portion of a plenum interior. The struts extend lengthwise between the gas path surfaces. Each strut has a cross-section geometry. The cross-section geometry has a center, and major and minor axes. The struts are circumferentially spaced apart from one another within the plenum. Each strut is oriented at a clocking angle theta. The clocking angle theta for each respective strut is disposed between the major axis of that strut and a line that intersects the cross-section geometry center of that strut and the axial centerline. At least one strut of the plurality of struts is oriented at a clocking angle theta that is greater than zero.
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