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公开(公告)号：US11572790B1
公开(公告)日：2023-02-07
申请号：US17454529
申请日：2021-11-11
发明人： Remo Marini , Panagiota Tsifourdaris , Nicolas Grivas , Daniel Lecuyer , Michael Papple , Robert Huszar , Othmane Leghzaouni , Jonathan Dorai , Jasrobin Grewal
摘要： A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.
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公开(公告)号：US10072577B2
公开(公告)日：2018-09-11
申请号：US15183074
申请日：2016-06-15
发明人： Remo Marini , Patrick Germain , Ljubisa Vrljes
CPC分类号： F02C7/185 , F01D25/24 , F02C6/08 , F02C7/14 , F05D2220/32 , F05D2250/51 , F05D2250/62 , F05D2260/213 , F05D2260/232 , Y02T50/676
摘要： A buffer air cooler system for gas turbine engines disposed in a bypass duct of the engine, includes a housing for containing the buffer air cooler therein and an inlet portion attached to the housing. In one embodiment, the inlet portion has a double-skin configuration in at least one region of a top, bottom and sides of the inlet portion.
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公开(公告)号：US10018150B2
公开(公告)日：2018-07-10
申请号：US15137257
申请日：2016-04-25
CPC分类号： F02K1/48 , F01D9/041 , F02K1/386 , F02K3/06 , F05D2210/40 , F05D2250/61
摘要： A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer for mixing exhaust gases with a bypass air stream, the TEC comprising an annular hub and the mixer surrounding the hub, and a plurality of deswirling struts circumferentially spaced apart with respect to a central axis of the TEC and located entirely within an axial length of the mixer. The mixer defines a trailing edge having one or more upstream-most locations thereof where the mixing of the exhausted gases and the bypass air stream begins to take place. The deswirling struts each extend radially across the annular exhaust gas duct and interconnect the mixer and the hub, defining a trailing edge positioned upstream of and axially spaced away from the one or more upstream-most locations of the trailing edge of the mixer.
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公开(公告)号：US09759159B2
公开(公告)日：2017-09-12
申请号：US14521888
申请日：2014-10-23
CPC分类号： F02K1/386 , F01D9/041 , F01D25/30 , F02K1/48 , F05D2240/12 , F05D2250/61
摘要： A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer in an annular wavy configuration having alternate crests and valleys, and a plurality of radial deswirling struts interconnecting an annular hub positioned within the mixer and selected valleys of the mixer. A plurality of secondary trailing edge struts smaller than the deswirling struts in average chord dimensions interconnect the annular hub and other selected valleys free of connection with the deswirling struts.
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公开(公告)号：US11536141B1
公开(公告)日：2022-12-27
申请号：US17649939
申请日：2022-02-04
发明人： Mohammed Ennacer , Panagiota Tsifourdaris , Remo Marini , Niloofar Moradi , Daniel Lecuyer , Patricia Phutthavong , Farzad Ashrafi
摘要： A turbine vane for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface. The surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.
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公开(公告)号：US11085333B2
公开(公告)日：2021-08-10
申请号：US13937587
申请日：2013-07-09
摘要： An exhaust mixer for a gas turbine engine where each outer lobe has at the downstream end a circumferential offset in a direction corresponding to that of the swirl component of the flow entering the mixer. The mixer has a crest line having at least a downstream portion curved with respect with respect to a circumferential direction of the mixer and/or a center line at the downstream end tilted with respect to a radial line extending to the tip of the outer lobe to define the circumferential offset. A method of mixing a core flow and a bypass flow surrounding the core flow with an annular mixer is also provided.
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公开(公告)号：US09163510B2
公开(公告)日：2015-10-20
申请号：US14303103
申请日：2014-06-12
摘要： The strut is for use in a gas turbine engine has body, typically having an airfoil shape, having a leading edge and a trailing edge. The leading edge has at least one gas inlet in direct fluid communication with at least one outlet located in the trailing edge through which gas may be redirected from the leading edge to the trailing edge through the strut for injection back into a wake region downstream of the strut.
摘要翻译： 支柱用于具有主体的燃气涡轮发动机，通常具有翼型形状，具有前缘和后缘。 前缘具有至少一个气体入口，其与位于后缘中的至少一个出口直接流体连通，通过该至少一个出口，气体可以通过支柱从前缘重新引导到后缘，用于注入到尾部的尾流区域 支撑。
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公开(公告)号：US20240328323A1
公开(公告)日：2024-10-03
申请号：US18129616
申请日：2023-03-31
发明人： Remo Marini , Christopher J. Gover
IPC分类号： F01D9/04
CPC分类号： F01D9/048 , F01D9/041 , F05D2240/12
摘要： A turbine scroll for use with an axial turbine is provided. The turbine scroll includes a flow channel, a scroll inlet, a plurality of stator vanes, and a plurality of vane passages. The flow channel is defined by an outer radial wall extending between first and second axial sidewalls that are spaced widthwise apart from one another. The stator vanes are disposed within the flow channel, spaced apart from one another, and are disposed around a circumference of the scroll. Each vane passage is defined between adjacent stator vanes. Each vane passage is open to an outer flow channel portion disposed radially between the stator vanes and the outer radial wall and is open to an annular region disposed radially inside of the stator vanes. The vane passages are configured to direct gas flow in an inwardly spiraling direction.
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公开(公告)号：US11578608B1
公开(公告)日：2023-02-14
申请号：US17454520
申请日：2021-11-11
发明人： Remo Marini , Marc Tardif , Jason Gillespie
摘要： A turbine vane for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface. The surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.
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公开(公告)号：US09982630B2
公开(公告)日：2018-05-29
申请号：US14721412
申请日：2015-05-26
发明人： Remo Marini , Roberto Marrano , Adam Trumpour
IPC分类号： F02K3/115 , F02K3/105 , B64D33/10 , F02C7/12 , F02C7/141 , B64D33/08 , F02C7/18 , F02C7/14 , F02K3/075 , F02K3/06 , B64D33/02 , F02K3/068 , F28D21/00 , F02C7/32 , F02K3/077 , F02K3/02 , F02K3/04 , F02K3/00 , F02K1/82 , F02K3/065 , F02C7/143 , F02K3/062
CPC分类号： F02K3/115 , B64D33/08 , B64D33/10 , B64D2033/024 , B64D2033/0286 , F02C7/12 , F02C7/14 , F02C7/141 , F02C7/143 , F02C7/18 , F02C7/185 , F02C7/32 , F02K1/822 , F02K3/00 , F02K3/025 , F02K3/04 , F02K3/06 , F02K3/062 , F02K3/065 , F02K3/068 , F02K3/075 , F02K3/077 , F02K3/105 , F05D2250/13 , F05D2250/50 , F05D2250/51 , F05D2250/52 , F05D2250/712 , F05D2260/20 , F05D2260/213 , F28D2021/0021 , F28D2021/0026 , F28D2021/0049 , Y02T50/671 , Y02T50/675
摘要： A cooler assembly disposed in and cooled by an air stream according to one embodiment includes a cooler matrix and a fairing. The fairing assembly is disposed generally around the cooler matrix and includes side fairing-housings, first and second side fairing-housings being joined to one another at respective leading and trailing edges, the leading edges partially defining a cooler inlet and the trailing edges partially defining a cooler outlet, the first and second side fairing-housing trailing edges angled transversely toward each other to define a trapezoidal shape for the outlet.
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