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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：US11118466B2
公开(公告)日：2021-09-14
申请号：US16165501
申请日：2018-10-19
发明人： Hien Duong , Vijay Kandasamy
摘要： A compressor of a gas turbine engine includes a rotor and a stator located downstream of the rotor. The stator has a plurality of vanes each with an airfoil extending span-wise between a root proximate an inner hub of the stator and a tip. A fillet is disposed at the leading edge of the root of the airfoil, and extends between a pressure side surface of the airfoil and the inner hub.
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公开(公告)号：US10900414B2
公开(公告)日：2021-01-26
申请号：US16199073
申请日：2018-11-23
发明人： Hien Duong , Karan Anand , Vijay Kandasamy , Rakesh Munlyappa
摘要： There is disclosed a fan assembly including a fan rotor including a hub and fan blades. The fan blades have a leading edge and a trailing edge. A fan stator downstream of the fan rotor relative to a direction of an airflow through the fan assembly. The fan stator includes vanes extending between radially inner ends and radially outer ends. A flow recirculation circuit has an inlet downstream of radially inner ends of the vanes of the fan stator and an outlet upstream of radially inner ends of the vanes. A recirculation stator has a plurality of stationary guide vanes circumferentially distributed around the axis and located in the flow recirculation circuit between the inlet and the outlet A method of operating the fan assembly is also disclosed.
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公开(公告)号：US10823197B2
公开(公告)日：2020-11-03
申请号：US15385435
申请日：2016-12-20
发明人： Hien Duong , Vijay Kandasamy , Saurabh S. Nair
摘要： A vane diffuser for diffusing gases is disclosed. The diffuser has an annular diffuser body including a plurality of diffuser vanes defining diffuser passages. The diffuser passages are circumferentially distributed. A direction of main gas flow through the diffuser passages is defined from a passage inlet in fluid communication with the outlet of the compressor to a passage outlet. A plurality of fluid injection conduits each extend between a conduit inlet and a conduit outlet for at least one of the diffuser vanes. The conduit outlet defines at least one opening in at least one of the pressure and suction side surfaces and is configured to inject fluid along one of the pressure and suction side surfaces in the direction of main gas flow through the corresponding diffuser passage.
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公开(公告)号：US10669854B2
公开(公告)日：2020-06-02
申请号：US15681003
申请日：2017-08-18
发明人： Hien Duong
摘要： An impeller comprises a hub and blades extending therefrom. The blades include splitter blades interspersed between full blades. First flow channels are defined between pressure sides of the splitter blades and suction sides of the full blades. Second flow channels are defined between suction sides of the splitter blades and pressure sides of the full blades. A width of the first flow channels at leading edges of the splitter blades and at the hub is less than a width of the second flow channels at the leading edges of the splitter blades and at the hub. The width of the first flow channels at the leading edges of the splitter blades and at the tips is more than the width of the second flow channels at the leading edges of the splitter blades and at the tips.
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公开(公告)号：US09765795B2
公开(公告)日：2017-09-19
申请号：US14469938
申请日：2014-08-27
发明人： Hien Duong , Krishna Prasad Balike , Thomas Veitch , Raman Warikoo , Keegan Lobo
CPC分类号： F04D29/384 , F01D5/141 , F01D5/145 , F04D19/00 , F04D19/02 , F04D29/324 , F05D2240/303 , F05D2270/17
摘要： A compressor rotor 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. A leading edge dihedral angle is defined at a point on the leading edge between a tangent to the airfoil and a vertical. The leading edge dihedral angle has a span-wise distribution. The distribution has at least one inflection point. A method of reducing a rub angle between a compressor rotor blade and a casing surrounding the blade is also presented.
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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：US09644639B2
公开(公告)日：2017-05-09
申请号：US14164494
申请日：2014-01-27
发明人： Hien Duong , Vijay Kandasamy
CPC分类号： F04D29/441 , F04D17/10 , F04D23/008 , F04D29/4206 , F04D29/685
摘要： The centrifugal compressor described includes an impeller shroud which encloses the impeller and has a curved shroud surface that extends between an inducer portion and an exducer portion. The compressor includes one or more circumferential grooves in the shroud body within the exducer portion. Each groove has opposed wall segments spaced apart therefrom. The wall segments are inclined at a nonzero groove angle relative to a normal of the shroud surface in a direction opposite the fluid flow path along the shroud surface.
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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：US12071959B1
公开(公告)日：2024-08-27
申请号：US18461705
申请日：2023-09-06
发明人： Hien Duong , Christopher Chiang
CPC分类号： F04D29/526 , F04D29/324 , F02C3/06 , F05D2220/323
摘要： A compressor for an aircraft engine, has: a gaspath extending around a central axis between a radially-inner wall and a radially-outer wall; a rotor having blades circumferentially distributed around the central axis, the blades having airfoils extending from roots to tips along a span and extending from leading edges to trailing edges along a chord, the airfoils extending across the gaspath; grooves defined in an inner face of the radially-outer wall, circumferentially distributed around the central axis, and having groove lengths extending in a first direction having a circumferential component relative to the central axis, the grooves located between the leading edges and the trailing edges of the airfoils; and slots defined in the inner face of the radially-outer wall, circumferentially distributed around the central axis, and having slot lengths extending in a second direction having an axial component relative to the central axis, the slots projecting from the grooves.
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