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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：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：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：US11041388B2
公开(公告)日：2021-06-22
申请号：US14673101
申请日：2015-03-30
发明人： Yau-Wai Li , Peter Townsend , Vijay Kandasamy
摘要： A gas turbine engine includes rotor having a hub, and a plurality of blades extending generally radially from the hub. Each of the blades has an airfoil portion. The airfoil portion has a leading edge and a trailing edge defining a chordwise direction, and a root and a tip defining a spanwise direction. Only a sub-set of the blades has a cutback at at least one of the trailing edge and the leading edge. A method of designing and a method of assembling a rotor having noise reduction properties in a gas turbine engine is also presented.
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公开(公告)号：US20180171871A1
公开(公告)日：2018-06-21
申请号：US15380205
申请日：2016-12-15
发明人： Hien Duong , Vijay Kandasamy , Rakesh Muniyappa
CPC分类号： F02C7/14 , F02C7/04 , F02K3/06 , F02K3/115 , F05D2260/213 , Y02T50/676
摘要： A gas turbine engine that comprises an engine core having a compressor, a turbine, a combustor, and a rotation axis. The engine further comprising a fan case wall having a radially-inner surface, a by-pass duct between the fan case wall and around the engine core, a plurality of struts circumferentially distributed and extending across the by-pass duct, a surface cooler adjacent to the radially-inner surface of the fan case and configured to be exposed to a by-pass air flow through the by-pass duct during operation of the gas turbine engine, the surface cooler fluidly communicating with a fluid circuit of the engine requiring cooling for of a fluid, and a recirculation conduit extending between an inlet in the radially-inner surface of the fan case disposed downstream of the surface cooler and an outlet in the radially-inner surface of the fan case wall disposed upstream of the surface cooler.
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公开(公告)号：US20140271108A1
公开(公告)日：2014-09-18
申请号：US13803418
申请日：2013-03-14
发明人： Hien Duong , Jason Nicholas , Peter Townsend , Vijay Kandasamy
IPC分类号： F02C9/18
CPC分类号： F02C9/18 , F01D5/145 , F04D27/023 , F04D29/526 , F04D29/682
摘要： A compressor for a gas turbine engine having a bleed air recirculation system includes a plurality of bleed holes extending through the shroud at a first axial location thereon substantially adjacent the blade tips. The bleed holes have a closed outer perimeter along their complete length. An annular bleed cavity surrounds the shroud and is in communication with outlet openings of the bleed holes. The bleed holes provide communication between said main gas flow passage and the bleed cavity. The bleed cavity includes exit passages having outlets disposed in said shroud at a second axial location which is upstream of both the first axial location and the leading edge of the blades of the rotor. Bleed air is passively bled from the main gas flow passage via the bleed holes, recirculated through the bleed cavity and re-injected back into the main gas flow passage at the second axial location.
摘要翻译： 具有排气再循环系统的燃气涡轮发动机的压缩机包括多个排放孔，其基本上邻近所述叶片尖端在其第一轴向位置延伸穿过所述护罩。 排放孔沿其完整长度具有封闭的外周。 环形排出腔围绕护罩并与排放孔的出口开口连通。 排放孔提供所述主气流通道和排出腔之间的连通。 排出腔包括出口通道，其具有在第二轴向位置处设置在所述护罩中的出口，该第二轴向位置在转子的叶片的第一轴向位置和前缘的上游。 排出的空气通过排放孔从主气流通道被动地排出，再循环通过排放腔，并在第二轴向位置再次注入主气流通道。
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公开(公告)号：US12055057B2
公开(公告)日：2024-08-06
申请号：US18091517
申请日：2022-12-30
发明人： Hien Duong , Vijay Kandasamy
CPC分类号： F01D25/162 , B64C21/02 , B64C21/025 , F01D5/145 , F01D9/02 , F04D29/682 , F04D29/684 , B64C2230/06 , B64C2230/20 , F04D29/324
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：US11572897B1
公开(公告)日：2023-02-07
申请号：US17374452
申请日：2021-07-13
发明人： Hien Duong , Vijay Kandasamy
摘要： A casing treatment for a compressor includes one or more cavities in a casing disposed radially outwardly of tips of the compressor rotor blades. A liner is moveable relative to the casing between a first position and a second position. The liner is shaped to add a volume to the tip clearance gap when moving from the second position toward the first position. The liner is displaceable between the first and second positions in coordination with at least the rotation of inlet guide vanes (IGVs) between IGV positions.
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