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21. 发明申请

US20140255197A1 ROTOR BLADES FOR GAS TURBINE ENGINES 有权
标题翻译：用于气体涡轮发动机的转子叶片
公开(公告)号：US20140255197A1
公开(公告)日：2014-09-11
申请号：US13789794
申请日：2013-03-08
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Hong YU
IPC分类号： F01D5/14
CPC分类号： F01D5/282 , F01D5/146 , F04D29/324 , F05D2220/36 , Y02T50/672 , Y02T50/673 , Y10T29/49332
摘要： A rotor dual-blade for a gas turbine engine that has a first blade component extending radially between a root and a tip and a second blade component, separate from the first component, extending radially between a root and a tip, wherein the second blade component is downstream, in series, of the first blade component and at least the first blade component is made of metal while the second blade component is a light weight composite material.
摘要翻译：一种用于燃气涡轮发动机的转子双叶片，其具有在根部和尖端之间径向延伸的第一叶片部件和与第一部件分离的第二叶片部件，其在根部和尖端之间径向延伸，其中第二叶片部件是第一叶片部件的串联下游，并且至少第一叶片部件由金属制成，而第二叶片部件是轻质复合材料。

22. 发明申请

US20140237987A1 GAS TURBINE ENGINE VARIABLE GEOMETRY FLOW COMPONENT 有权
标题翻译：气体涡轮发动机可变几何流量组件
公开(公告)号：US20140237987A1
公开(公告)日：2014-08-28
申请号：US14090953
申请日：2013-11-26
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc.
发明人： Matthew J. Bloxham , Craig E. Heathco , Adam D. Ford , Robert T. Duge , Thomas I. Gorman
IPC分类号： F01D17/14 , F01D5/18
CPC分类号： F01D17/14 , F01D5/146 , F01D5/186 , Y02T50/673
摘要： A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.
摘要翻译：公开了适用于燃气涡轮发动机的可变几何机构，其中联接到可旋转环（或环）的可动叶片段用于改变流过燃气涡轮发动机的工作流体的空气动力特性。可移动叶片段可以在与第一叶片相关联的第一位置和与第二叶片相关联的第二位置之间旋转穿过环或环，以将可动叶片段放置在第一和第二叶片中的一个或另一个附近燃气涡轮发动机的叶片。可移动的叶片段可用于改变其他方面的弯度，出口流动面积，并且可用于影响和/或适应诸如入射角和旋转角度的特性。

23. 发明授权

US08672618B2 Multi-vane variable stator unit of a fluid flow machine 有权
标题翻译：流体流动机的多叶片可变定子单元
公开(公告)号：US08672618B2
公开(公告)日：2014-03-18
申请号：US12609633
申请日：2009-10-30
申请人： Volker Guemmer
发明人： Volker Guemmer
IPC分类号： F01D9/02
CPC分类号： F04D29/563 , F01D5/146 , F01D17/162 , F04D29/644
摘要： A fluid flow machine has a main flow path which is confined by a hub (3) and a casing (2) and in which at least one row of variable stator vanes (1) is arranged. The stator vanes (1) are rotatably borne around a rotary axis 4. On at least one of the hub (3) and the casing (2), at least one arrangement with at least two stator vanes (1) connected to a common rotary base (5) is provided, such that the at least two stator vanes (1) are rotatable around the rotary axis (4) when this multi-vane variable stator unit is varied.
摘要翻译：流体流动机具有由轮毂（3）和壳体（2）限制的主流路，并且其中布置有至少一排可变定子叶片（1）。定子叶片（1）围绕旋转轴线4可转动地支承。在轮毂（3）和壳体（2）中的至少一个上，具有至少两个定子叶片（1）的连接至公共旋转基座（5）设置成使得当该多叶片可变定子单元变化时，至少两个定子叶片（1）能够围绕旋转轴线（4）旋转。

24. 发明授权

US08257023B2 Fan blade 有权
标题翻译：风机叶片
公开(公告)号：US08257023B2
公开(公告)日：2012-09-04
申请号：US12055615
申请日：2008-03-26
申请人： Olivier Belmonte , Amadou Lamine M'Bengue
发明人： Olivier Belmonte , Amadou Lamine M'Bengue
IPC分类号： F01D5/04
CPC分类号： F04D19/022 , F01D5/146 , F01D5/147 , F05D2220/326 , F05D2220/327 , Y02T50/671 , Y02T50/673
摘要： The present invention relates to the field of blades, particularly fan blades, intended for turbojets, particularly of the aeronautical type. Its objective is to provide a fan blade the features of which will enable the number of fan blades to be reduced while at the same time providing satisfactory performance. According to the invention, the fan blade comprises a plurality of aerodynamic parts which are superposed in a radial direction Z and the number of aerodynamic profiles varies from one aerodynamic part to the other.
摘要翻译：本发明涉及用于涡轮喷气发动机，特别是航空类型的叶片领域，特别是风扇叶片领域。其目的是提供一种风扇叶片，其特征在于能够减少风扇叶片的数量，同时提供令人满意的性能。根据本发明，风扇叶片包括多个空气动力部件，它们沿径向Z重叠，并且空气动力学轮廓的数量从一个空气动力部分变化到另一个。

25. 发明授权

US08021113B2 Twin-airfoil blade with spacer strips 有权
标题翻译：双翼型叶片带间隔条
公开(公告)号：US08021113B2
公开(公告)日：2011-09-20
申请号：US12351323
申请日：2009-01-09
申请人： Pascal Routier
发明人： Pascal Routier
IPC分类号： F01D5/30
CPC分类号： F01D9/041 , F01D5/146 , F04D29/681 , F05B2240/33 , F05D2240/12 , F05D2240/126
摘要： The invention relates to a blade possessing a leading edge and a trailing edge, the blade comprising a first airfoil possessing an inner face and an outer face extending between said leading edge and said trailing edge, a second airfoil possessing an inner face and an outer face extending between said leading edge and said trailing edge, and at least one spacer strip interconnecting said inner face of the first airfoil and said inner face of the second airfoil, said at least one strip extending to said trailing edge, the distance between the inner face of the first airfoil and the inner face of the second airfoil being of the same order of magnitude as the maximum thickness of the first or the second airfoil.
摘要翻译：本发明涉及具有前缘和后缘的叶片，该叶片包括具有内表面的第一翼型件和在所述前缘和所述后缘之间延伸的外表面，第二翼型件具有内表面和外表面在所述前缘和所述后缘之间延伸，以及至少一个间隔条，其将所述第一翼面的所述内表面和所述第二翼面的所述内表面相互连接，所述至少一个条延伸到所述后缘，所述内表面之间的距离的第一翼型件和第二翼型件的内表面具有与第一或第二翼型件的最大厚度相同数量级。

26. 发明申请

US20100303629A1 FLUID FLOW MACHINE WITH A BLADE ROW GROUP FEATURING A MERIDIONAL EDGE DISTANCE 有权
标题翻译：带叶片组的流体流量计特征在一个边缘边距
公开(公告)号：US20100303629A1
公开(公告)日：2010-12-02
申请号：US12771596
申请日：2010-04-30
申请人： Volker GUEMMER
发明人： Volker GUEMMER
IPC分类号： F01D5/14
CPC分类号： F01D5/146 , F01D5/142 , F01D9/041 , F04D29/544 , F04D29/563 , Y02T50/671 , Y02T50/673
摘要： A main flow path of a fluid flow machine includes N adjacent member blade rows firmly arranged relative to each other in both a meridional direction m and a circumferential direction u. A number of the member blade rows, N, is greater than/equal to 2 and (i) designates a running index with values between 1 and N. A trailing edge HK (i) of a blade of the member blade row (i) is spaced from a leading edge VK(i+1) of a blade of the adjacent, downstream member blade row (i+1) by a meridional edge distance D in a meridional plane established by axial direction x and radial direction r. A value of D along a height of the main flow path increases towards the main flow path confinement at least along a part of the area between the main flow path center and the main flow path confinement.
摘要翻译：流体流动机的主流路包括在子午方向m和圆周方向u上相对于彼此牢固地布置的N个相邻的构件叶片排。多个构件叶片排N大于/等于2，（i）表示值在1和N之间的行程指数。构件叶片排（i）的叶片的后缘HK（i）在相邻的下游构件叶片排（i + 1）的叶片的前缘VK（i + 1）上通过由轴向方向x和径向r建立的子午线中的子午线距离D隔开。至少沿着主流路中心与主流路限制之间的区域的一部分，沿着主流路的高度的D的值朝向主流路限制增加。

27. 发明申请

US20100260591A1 Spanwise split variable guide vane and related method 审中-公开
标题翻译：分段可变导叶及相关方法
公开(公告)号：US20100260591A1
公开(公告)日：2010-10-14
申请号：US11808314
申请日：2007-06-08
申请人： Nick Martin , Steven M. Schirle , Stephen P. Wassynger , Robert Zacharias
发明人： Nick Martin , Steven M. Schirle , Stephen P. Wassynger , Robert Zacharias
IPC分类号： F01D17/16 , F04D29/56
CPC分类号： F01D17/162 , F01D5/146 , F04D29/563 , F05D2250/311 , Y02T50/673
摘要： Accordingly, in one aspect, the invention relates to a variable guide vane for an axial flow compressor comprising: a first radially outer vane section; and a second radially inner vane section; the first and second vane sections angularly adjustable relative to each other about a longitudinal radial axis of the vane.
摘要翻译：因此，一方面，本发明涉及一种用于轴流式压缩机的可变导叶，包括：第一径向外叶片部分; 和第二径向内叶片部分; 所述第一和第二叶片部分围绕所述叶片的纵向径向轴线可相对于彼此成角度地调节。

28. 发明申请

US20100158684A1 VANE ASSEMBLY CONFIGURED FOR TURNING A FLOW IN A GAS TURBINE ENGINE, A STATOR COMPONENT COMPRISING THE VANE ASSEMBLY, A GAS TURBINE AND AN AIRCRAFT JET ENGINE 审中-公开
标题翻译：用于在气体涡轮发动机中旋转流动的VANE组件，包括VANE组件，气体涡轮机和飞机喷射发动机的定子组件
公开(公告)号：US20100158684A1
公开(公告)日：2010-06-24
申请号：US12514800
申请日：2006-11-14
申请人： Stephane Baralon
发明人： Stephane Baralon
IPC分类号： F01D9/02
CPC分类号： F01D9/041 , F01D5/146 , F01D9/065 , Y02T50/673
摘要： A vane assembly configured for turning a flow in a gas turbine engine includes a stationary main guide vane and an additional guide vane, wherein a leading edge of the additional guide vane is positioned upstream of a leading edge of the main guide vane and wherein the additional guide vane extends a distance along the main guide vane towards a trailing edge of the main guide vane forming a passageway between the additional guide vane and the main guide vane.
摘要翻译：构造成用于转动燃气涡轮发动机中的流动的叶片组件包括固定的主导向叶片和附加的导向叶片，其中附加导向叶片的前缘位于主导叶的前缘的上游，导向叶片沿主导叶向着主导叶片的后缘延伸一段距离，形成在附加导流叶片和主导叶片之间的通道。

29. 发明授权

US07665964B2 Turbine 有权
标题翻译：涡轮
公开(公告)号：US07665964B2
公开(公告)日：2010-02-23
申请号：US11176348
申请日：2005-07-08
申请人： Mark D Taylor , Neil W Harvey , Martin G Rose
发明人： Mark D Taylor , Neil W Harvey , Martin G Rose
IPC分类号： F01D1/10
CPC分类号： F01D5/145 , F01D5/143 , F01D5/146 , F01D5/225 , F01D9/041 , F01D11/08 , F05D2270/17
摘要： A gas turbine engine turbine comprises an annular array of nozzle guide vanes and an annular array of turbine blades mounted within its annular casing. An array of radially extending protrusions are positioned axially upstream of said array of said nozzle guide vanes and protruding inwardly from the inner casing wall so as to mix the tangential momentum component of the overtip leakage fluid flow before it reaches the array of nozzle guide vanes.
摘要翻译：燃气涡轮发动机涡轮机包括喷嘴导向叶片的环形阵列和安装在其环形壳体内的涡轮叶片的环形阵列。径向延伸的突起的阵列位于所述喷嘴导向叶片的所述阵列的轴向上游并从内壳壁向内突出，从而在溢流泄漏流体流到达喷嘴导叶阵列之前混合切向动量分量。

30. 发明申请

US20090220348A1 TWIN-AIRFOIL BLADE WITH SPACER STRIPS 有权
标题翻译：带空隙条的双叶片叶片
公开(公告)号：US20090220348A1
公开(公告)日：2009-09-03
申请号：US12351323
申请日：2009-01-09
申请人： Pascal ROUTIER
发明人： Pascal ROUTIER
IPC分类号： F01D5/14
CPC分类号： F01D9/041 , F01D5/146 , F04D29/681 , F05B2240/33 , F05D2240/12 , F05D2240/126
摘要： The invention relates to a blade possessing a leading edge and a trailing edge, the blade comprising a first airfoil possessing an inner face and an outer face extending between said leading edge and said trailing edge, a second airfoil possessing an inner face and an outer face extending between said leading edge and said trailing edge, and at least one spacer strip interconnecting said inner face of the first airfoil and said inner face of the second airfoil, said at least one strip extending to said trailing edge, the distance between the inner face of the first airfoil and the inner face of the second airfoil being of the same order of magnitude as the maximum thickness of the first or the second airfoil.
摘要翻译：本发明涉及具有前缘和后缘的叶片，该叶片包括具有内表面的第一翼型件和在所述前缘和所述后缘之间延伸的外表面，第二翼型件具有内表面和外表面在所述前缘和所述后缘之间延伸，以及至少一个间隔条，其将所述第一翼面的所述内表面和所述第二翼面的所述内表面相互连接，所述至少一个条延伸到所述后缘，所述内表面之间的距离的第一翼型件和第二翼型件的内表面具有与第一或第二翼型件的最大厚度相同数量级。

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