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公开(公告)号：US09249666B2
公开(公告)日：2016-02-02
申请号：US13334609
申请日：2011-12-22
CPC分类号： F01D5/141 , F01D9/041 , F03D1/0633 , F04D29/324 , F05B2250/611 , F05D2220/36 , F05D2240/121 , F05D2240/303 , F05D2250/184 , F05D2250/611 , Y02E10/721 , Y02E10/726 , Y02T50/671 , Y02T50/673 , Y10T29/49316 , Y10T29/49321 , Y10T29/49323 , Y10T29/49332 , Y10T29/49336 , Y10T137/0536
摘要： An airfoil and method of fabricating an airfoil including a first and a second side coupled at a leading and a trailing edge and extending there between. The airfoil includes a plurality of first chord sections having a first chord length and extending outward from one of the first side or second side at the leading edge and a plurality of second chord sections having a second chord length and extending outward from the one of the first side or the second side at the leading edge. The leading edge including spaced-apart wave-shaped projections defining a waveform. The configuration defining a three-dimensional crenulated airfoil configured to facilitate desensitization of an airfoil unsteady pressure response to at least one impinging upstream generated wake or vortex by decorrelating spatially and temporally and reducing in amplitude an unsteady pressure caused by interaction of the airfoil with the upstream generated wake or vortex.
摘要翻译： 翼型件和制造翼型件的方法，该翼型件包括在前缘和后缘处连接并在其之间延伸的第一和第二侧面。 翼型件包括多个具有第一弦长并且在前缘处从第一侧或第二侧中的一个向外延伸的第一弦弦部分和具有第二弦长并且从第一弦长部分 第一侧或第二侧在前缘。 前缘包括限定波形的间隔开的波浪形突起。 该构造限定了三维经过旋转的翼型，其被配置为促进翼型对于至少一个撞击上游产生的尾流或涡流的翼型的非均匀压力响应，通过在空间和时间上解相关并且降低振幅，由翼型件与上游的相互作用引起的不稳定压力 产生尾流或涡流。
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2.发明授权Airfoils including tip profile for noise reduction and method for fabricating same 有权包括用于降噪的尖端轮廓的翼型及其制造方法公开(公告)号：US09102397B2
公开(公告)日：2015-08-11
申请号：US13330766
申请日：2011-12-20
申请人： Trevor Howard Wood
发明人： Trevor Howard Wood
CPC分类号： F01D5/141 , B64C11/18 , B64C11/48 , B64D2027/005 , F01D1/26 , F01D5/20 , F04D19/024 , F04D29/164 , F04D29/324 , F04D29/681 , F05D2220/36 , F05D2240/307 , F05D2250/712 , Y02E10/72 , Y02E10/722 , Y02T50/66 , Y02T50/671 , Y02T50/673 , Y10T29/49336
摘要： An airfoil, a fan assembly and an unducted contra-rotating fan engine include fabricating at least one airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil includes a plurality of chord sections having a chord length. The airfoil including a tip profile defining a reducing slope extending from the leading edge at the tip portion along at least a portion of the chord length. The tip profile is configured to reduce the high unsteady pressure near the tip portion of the airfoil.
摘要翻译： 翼型件，风扇组件和未引导的反转风扇发动机包括制造至少一个翼型件，其包括在前缘和后缘处连接在一起并在其间延伸的吸力和压力侧。 翼型件包括具有弦长的多个弦杆部分。 所述翼型件包括尖端轮廓，其限定沿着所述弦长的至少一部分从所述尖端部分处的所述前缘延伸的减小斜面。 顶端轮廓被配置为减小靠近翼型的末端部分的高不稳定压力。
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公开(公告)号：US08083487B2
公开(公告)日：2011-12-27
申请号：US11774762
申请日：2007-07-09
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F04D29/324 , F05D2240/301 , F05D2250/184 , Y02T50/671 , Y02T50/673 , Y10T29/49336
摘要： A method of fabricating an airfoil is provided. The method includes fabricating at least one airfoil including a suction side and a pressure side coupled together at a leading edge and a trailing edge, wherein the airfoil includes a plurality of first and second chord sections each extending between the trailing and leading edges, wherein at least one of the first chord sections extends outward from the pressure side of the airfoil at the trailing edge, and at least one of the second chord sections extends outward from the suction side of the airfoil at the trailing edge.
摘要翻译： 提供一种制造翼型的方法。 该方法包括制造至少一个翼型件，其包括在前缘和后缘处联接在一起的吸入侧和压力侧，其中翼型件包括多个第一和第二弦杆部分，每个翼弦部分在后缘和前缘之间延伸，其中在 第一和弦部分中的至少一个弦部分在后缘处从翼型的压力侧向外延伸，并且至少一个第二弦部分在后缘处从翼型的吸力侧向外延伸。
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公开(公告)号：US08333552B2
公开(公告)日：2012-12-18
申请号：US12416950
申请日：2009-04-02
CPC分类号： F01D25/162 , F01D5/145 , F01D5/147 , F01D5/16 , F01D9/041 , F01D9/065 , F02C7/14 , F02C7/18 , F02K3/06 , F05D2260/22141 , F05D2260/96 , F05D2270/17 , F05D2300/612 , Y02T50/672 , Y02T50/673 , Y02T50/676 , Y10T29/4932
摘要： An outlet guide vane assembly for turbomachines is provided. The outlet guide vane assembly comprises one or more outlet guide vanes, wherein each of the one or more outlet guide vanes comprises a first surface and a second surface, and wherein the one or more outlet guide vanes are disposed between an inner wall and an outer wall of an engine and a surface cooler layer disposed on at least a portion of the first surface, the second surface, or both of the one or more outlet guide vanes, wherein the surface cooler layer comprises a metal foam, a carbon foam, or a combination thereof, wherein the metal foam, the carbon foam or the combination thereof is configured to augment heat transfer and enhance acoustic absorption.
摘要翻译： 提供了一种用于涡轮机的出口导叶组件。 出口导叶组件包括一个或多个出口导向叶片，其中一个或多个出口导向叶片中的每一个包括第一表面和第二表面，并且其中一个或多个出口导向叶片设置在内壁和外部之间 发动机的壁和设置在所述第一表面，第二表面或所述一个或多个出口导向叶片的至少一部分上的表面冷却器层，其中所述表面冷却器层包括金属泡沫，碳泡沫或 其组合，其中金属泡沫，碳泡沫或其组合构造成增加热传递和增强声吸收。
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公开(公告)号：US09121294B2
公开(公告)日：2015-09-01
申请号：US13331301
申请日：2011-12-20
CPC分类号： F01D5/282 , F01D5/141 , F05D2220/36 , F05D2240/304 , F05D2250/184 , Y02T50/672 , Y02T50/673
摘要： A gas turbine engine airfoil includes leading and trailing edges, pressure and suction sides extending from airfoil base to airfoil tip, trailing edge cladding made of cladding material bonded to composite core made of composite material, cladding material less brittle than composite material, composite core including central core portion extending downstream from leading edge portion to trailing edge portion of composite core, and trailing edge cladding including wavy wall and trailing edge. Pressure and suction side flanks of trailing edge cladding may be bonded to pressure and suction side surfaces of trailing edge portion. Waves of wavy wall may extend normal to and away from the pressure and suction side surfaces. Trailing edge cladding may include wavy pressure and suction side trailing edge guards including waves of wavy wall. Airfoil may extend outwardly from platform of a blade. Root may include integral dovetail.
摘要翻译： 燃气涡轮发动机翼型包括前缘和后缘，压力和吸力侧从翼型基部延伸到翼面，由复合材料复合芯结合的包层材料制成的后缘包层，比复合材料脆的包层材料，复合芯包括 中心芯部分延伸到复合芯的前缘部分到后缘部分的下游，以及包括波浪壁和后缘的后缘包层。 后缘包层的压力和吸力侧面可以结合到后缘部分的压力和吸力侧表面。 波浪形波浪的波浪可以垂直于和远离压力和吸力侧表面延伸。 后缘包层可能包括波浪压力和吸力侧后缘护罩，包括波浪形波浪。 翼型件可以从叶片的平台向外延伸。 根可以包括整体的燕尾。
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公开(公告)号：US20130164488A1
公开(公告)日：2013-06-27
申请号：US13334609
申请日：2011-12-22
CPC分类号： F01D5/141 , F01D9/041 , F03D1/0633 , F04D29/324 , F05B2250/611 , F05D2220/36 , F05D2240/121 , F05D2240/303 , F05D2250/184 , F05D2250/611 , Y02E10/721 , Y02E10/726 , Y02T50/671 , Y02T50/673 , Y10T29/49316 , Y10T29/49321 , Y10T29/49323 , Y10T29/49332 , Y10T29/49336 , Y10T137/0536
摘要： An airfoil and method of fabricating an airfoil including a first and a second side coupled together at a leading and a trailing edge and extending there between. The airfoil includes a plurality of first chord sections having a first chord length and extending outward from one of the first side or second side of the airfoil at the leading edge and a plurality of second chord sections having a second chord length and extending outward from the one of the first side or the second side of the airfoil at the leading edge. The leading edge including spaced-apart wave-shaped projections defining a waveform. The configuration defining a three-dimensional crenulated airfoil configured to facilitate desensitization of an airfoil unsteady pressure response to at least one impinging upstream generated wake or vortex by decorrelating spatially and temporally and reducing in amplitude an unsteady pressure caused by interaction of the airfoil with the upstream generated wake or vortex.
摘要翻译： 一种翼型件和制造翼型件的方法，该翼型件包括在前缘和后缘处连接在一起并在其之间延伸的第一和第二侧面。 翼型件包括多个具有第一弦长并且在前缘处从翼型的第一侧或第二侧之一向外延伸的第一弦弦部分和多个具有第二弦长并从该翼型向外延伸的第二弦弦部分 在前缘的翼型的第一侧或第二侧之一。 前缘包括限定波形的间隔开的波浪形突起。 该构造限定了三维经过旋转的翼型，其被配置为促进翼型对于至少一个撞击上游产生的尾流或涡流的翼型的非均匀压力响应，通过在空间和时间上解相关并且降低振幅，由翼型件与上游的相互作用引起的不稳定压力 产生尾流或涡流。
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公开(公告)号：US20090025393A1
公开(公告)日：2009-01-29
申请号：US11590041
申请日：2006-10-31
申请人： Karl Edward Sheldon , Charles Erklin Seeley , Ludwig Christian Haber , Trevor Howard Wood , Jonathan Glenn Luedke , Chingwei Michael Shieh
发明人： Karl Edward Sheldon , Charles Erklin Seeley , Ludwig Christian Haber , Trevor Howard Wood , Jonathan Glenn Luedke , Chingwei Michael Shieh
CPC分类号： B64D33/02 , B64D41/00 , B64D2033/0206 , B64D2033/0213 , B64D2041/002 , F02C7/045 , F02C7/32 , F05D2220/50 , F05D2260/962 , F05D2270/101 , Y02T50/672
摘要： An embodiment of the technology described herein is an auxiliary power unit assembly. The auxiliary power unit assembly includes an auxiliary power unit being installable in an aircraft having a cabin, a duct connecting the cabin and the auxiliary power unit, and a noise reduction feature in the duct.
摘要翻译： 本文描述的技术的实施例是辅助动力单元组件。 辅助动力单元组件包括可安装在具有舱室的飞行器中的辅助动力单元，连接舱室和辅助动力单元的管道以及管道中的降噪特征。
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公开(公告)号：US09938931B2
公开(公告)日：2018-04-10
申请号：US12342466
申请日：2008-12-23
CPC分类号： F02K1/827 , F01D25/12 , F02C7/045 , F02C7/12 , F05D2300/224 , F05D2300/612 , Y02T50/675 , Y10T29/4935
摘要： A surface cooler for turbomachines includes an inner layer and an outer layer disposed adjacent to the inner layer and including a metal foam, a carbon foam, or a combination thereof, wherein the metal foam, the carbon foam or a combination thereof is configured to augment heat transfer and enhance acoustic absorption. Further, the outer layer includes a plurality of fins, wherein the plurality of fins are configured to augment heat transfer and enhance acoustic absorption, and wherein the plurality of fins includes metal foam, a carbon foam, or a combination thereof.
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公开(公告)号：US20130156592A1
公开(公告)日：2013-06-20
申请号：US13331301
申请日：2011-12-20
IPC分类号： F01D5/14
CPC分类号： F01D5/282 , F01D5/141 , F05D2220/36 , F05D2240/304 , F05D2250/184 , Y02T50/672 , Y02T50/673
摘要： A gas turbine engine airfoil includes leading and trailing edges, pressure and suction sides extending from airfoil base to airfoil tip, trailing edge cladding made of cladding material bonded to composite core made of composite material, cladding material less brittle than composite material, composite core including central core portion extending downstream from leading edge portion to trailing edge portion of composite core, and trailing edge cladding including wavy wall and trailing edge. Pressure and suction side flanks of trailing edge cladding may be bonded to pressure and suction side surfaces of trailing edge portion. Waves of wavy wall may extend normal to and away from the pressure and suction side surfaces. Trailing edge cladding may include wavy pressure and suction side trailing edge guards including waves of wavy wall. Airfoil may extend outwardly from platform of a blade. Root may include integral dovetail.
摘要翻译： 燃气涡轮发动机翼型包括前缘和后缘，压力和吸力侧从翼型基部延伸到翼面，由复合材料复合芯结合的包层材料制成的后缘包层，比复合材料脆的包层材料，复合芯包括 中心芯部分延伸到复合芯的前缘部分到后缘部分的下游，以及包括波浪壁和后缘的后缘包层。 后缘包层的压力和吸力侧面可以结合到后缘部分的压力和吸力侧表面。 波浪形波浪的波浪可以垂直于和远离压力和吸力侧表面延伸。 后缘包层可能包括波浪压力和吸力侧后缘护罩，包括波浪形波浪。 翼型件可以从叶片的平台向外延伸。 根可以包括整体的燕尾。
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公开(公告)号：US08419372B2
公开(公告)日：2013-04-16
申请号：US13214671
申请日：2011-08-22
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F04D29/324 , F05D2240/301 , F05D2250/184 , Y02T50/671 , Y02T50/673 , Y10T29/49336
摘要： An airfoil of varying span-wise thickness comprising a suction side and a pressure side coupled together at a leading edge and a trailing edge, with the trailing edge comprising a plurality of spaced-apart wave-shaped projections. Exemplary embodiments provide airfoil geometry and/or trailing edge features to influence downstream wake flow. Methods of fabricating an airfoil for improved wake flow are also provided.
摘要翻译： 具有不同跨度的厚度的翼型包括在前缘和后缘处联接在一起的吸力侧和压力侧，其后缘包括多个间隔开的波浪形突起。 示例性实施例提供翼型件几何形状和/或后缘特征以影响下游尾流。 还提供了制造用于改善尾流的翼型的方法。
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