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公开(公告)号：US20240218809A1
公开(公告)日：2024-07-04
申请号：US18091517
申请日：2022-12-30
发明人： Hien Duong , Vijay Kandasamy
CPC分类号： F01D25/162 , F01D9/02
摘要： A strut includes a strut body extending in a radial direction and defining an airfoil shape in cross-section perpendicular to the radial direction. The airfoil shape includes a leading edge and a trailing edge. An extraction inlet is defined through an exterior surface of the strut body, in fluid communication with an internal conduit of the strut body. An injection outlet is defined through the exterior surface of the strut body, in fluid communication with the internal conduit for fluid communication through the internal conduit from the extraction inlet to the injection outlet.
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公开(公告)号：US11286951B2
公开(公告)日：2022-03-29
申请号：US16418263
申请日：2019-05-21
发明人： Hien Duong
摘要： A diffuser pipe is disclosed having a tubular body including 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. The pipe outlet is scalloped.
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公开(公告)号：US10718215B2
公开(公告)日：2020-07-21
申请号：US15808060
申请日：2017-11-09
发明人： Raman Warikoo , Krishna Prasad Balike , Keegan Lobo , Hien Duong , Thomas Veitch
摘要： An airfoil for a gas turbine engine comprises at least three successive sections defined between a root and a tip. A first decrease of maximum thickness-to-chord ratios defined by a difference between a maximum thickness-to-chord ratio at the root and a maximum thickness-to-chord ratio at a first spanwise position, a second decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the first spanwise position and a maximum thickness-to-chord ratio at a second spanwise position, a third decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the second spanwise position and a maximum thickness-to-chord ratio at the tip, the second decrease being greater than the corresponding first and third decreases.
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公开(公告)号：US10570925B2
公开(公告)日：2020-02-25
申请号：US14924082
申请日：2015-10-27
发明人： Hien Duong , Vijay Kandasamy , Koundinya Upadrasta
IPC分类号： F04D29/54
摘要： A compressor diffuser for a gas turbine engine includes one or more diffuser pipes having a tubular body defining an internal flow passage extending therethrough. The tubular body includes a first portion extending in a first direction, a second portion extending in a second direction different from the first direction, and a curved portion fluidly linking the first portion and the second portion. A splitter vane is disposed within the internal flow passage of the curved portion of the tubular body, the splitter vane defining a convergent flow passage between itself and a radially inner wall of the curved portion.
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公开(公告)号：US09810157B2
公开(公告)日：2017-11-07
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.
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公开(公告)号：US20140260324A1
公开(公告)日：2014-09-18
申请号：US13803368
申请日：2013-03-14
发明人： Hien Duong , Jason Nichols , Vijay Kandasamy
摘要： A rotor for a gas turbine engine includes a plurality of radially extending blades, each having a remote blade tip defining an outer tip surface, and a leading edge defined between opposed pressure and suction side airfoil surfaces. A shroud circumferentially surrounds the rotor, and a radial distance between an inner surface of the shroud and the outer tip surface of the blades defines a radial tip clearance gap therebetween. The tip of each of the blades has a pressure side edge formed at the intersection between the outer tip surface and the pressure side airfoil surface, and a suction side edge formed at the intersection between the outer tip surface and the pressure side airfoil surface. The suction side edge has a larger radius of curvature than the pressure side edge, thereby reducing the amount of tip leakage flow through the radial tip clearance gap.
摘要翻译： 用于燃气涡轮发动机的转子包括多个径向延伸的叶片，每个叶片具有限定外部尖端表面的远程叶片尖端和限定在相对的压力和吸力侧翼面之间的前缘。 护罩周向地围绕转子，并且护罩的内表面和刀片的外尖端表面之间的径向距离限定了它们之间的径向顶端间隙。 每个叶片的尖端具有形成在外端头表面和压力侧翼型件表面之间的交叉点处的压力侧边缘，以及形成在外端头表面和压力侧翼型件表面之间的交叉处的吸力侧边缘。 吸力侧边缘具有比压力侧边缘更大的曲率半径，从而减少通过径向顶端间隙的尖端泄漏量。
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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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公开(公告)号：US11639666B2
公开(公告)日：2023-05-02
申请号：US17466208
申请日：2021-09-03
发明人： Hien Duong , Vijay Kandasamy
摘要： A fluid machine for an aircraft engine has: first and second walls; a gaspath defined between the first wall and the second wall; a rotor having blades rotatable about the central axis; and a stator having: a row of vanes having airfoils including leading edges, trailing edges, pressure sides and suction sides opposed the pressure sides, and depressions defined in the first wall, the depressions extending from a baseline surface of the first wall away from the second wall, a depression of the depressions located circumferentially between a pressure side of the pressure sides and a suction side of the suction sides, the depression axially overlapping the airfoils and located closer to the suction side than to the pressure side, an upstream end of the depression located closer to a leading edge of the leading edges than to a trailing edge of the trailing edges.
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公开(公告)号：US10781705B2
公开(公告)日：2020-09-22
申请号：US16201255
申请日：2018-11-27
发明人： Jason Nichols , Thomas Veitch , Peter Townsend , Hien Duong , Guiherme Watson
摘要： An inter-compressor case for a gas turbine engine is disclosed. The inter-compressor case comprises: an outer casing and an inner casing radially spaced apart relative to a longitudinal axis; a gas path extending from a plurality of radial inlets arranged in a circumferentially spaced apart array around the outer casing to an annular outlet defined by an axially extending downstream portion of the outer casing and an axially extending downstream portion of the inner casing; a plurality of struts having a gas path surface extending across the gas path between the outer casing and the inner casing; and a plurality of flow separators extending from the adjacent radial inlets. The flow separators have trailing edges disposed upstream of the annular outlet and include a plurality of full length flow separators and a plurality of truncated flow separators.
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公开(公告)号：US10393019B2
公开(公告)日：2019-08-27
申请号：US15222307
申请日：2016-07-28
发明人： Hien Duong
摘要： Assemblies and methods for providing injection air to influence flow in a flow passage defined by a fan of a gas turbine engine are disclosed. In one embodiment, the method comprises: receiving air into an interior of a nose cone; increasing the pressure of the air in the interior of the nose cone and directing the pressurized air; and discharging the air into the flow passage defined by the fan.
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