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1. 发明申请

US20070258818A1 Airfoil array with an endwall depression and components of the array 有权
标题翻译：翼型阵列具有端壁凹陷和阵列的部件
公开(公告)号：US20070258818A1
公开(公告)日：2007-11-08
申请号：US11415898
申请日：2006-05-02
申请人： Eunice Allen-Bradley , Eric Grover , Thomas Praisner , Joel Wagner
发明人： Eunice Allen-Bradley , Eric Grover , Thomas Praisner , Joel Wagner
IPC分类号： F01D11/00
CPC分类号： F01D5/145 , F01D5/143 , F01D9/041 , F05D2240/80 , F05D2250/291 , F05D2250/60
摘要： An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28 or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages 74. The endwall has a trough 100 toward a pressure side of the passage and a more elevated profile toward a suction side of the passage for reducing secondary flow losses.
摘要翻译：翼型阵列包括横向延伸的端壁56，其具有从端壁突出的一系列诸如28或38的翼型件。翼型件与端壁配合以限定一系列流体流动通道74。端壁具有朝向通道的压力侧的槽100，并且朝向通道的吸入侧具有更高的轮廓，以减少二次流动损失。

2. 发明申请

US20070258819A1 Airfoil array with an endwall protrusion and components of the array 有权
标题翻译：翼型阵列具有端壁突起和阵列的部件
公开(公告)号：US20070258819A1
公开(公告)日：2007-11-08
申请号：US11415915
申请日：2006-05-02
申请人： Eunice Allen-Bradley , Eric Grover , Thomas Praisner , Joel Wagner
发明人： Eunice Allen-Bradley , Eric Grover , Thomas Praisner , Joel Wagner
IPC分类号： F01D11/00
CPC分类号： F01D5/145 , F01D5/143 , F01D9/041 , F05D2240/121 , F05D2240/303 , F05D2240/90 , F05D2250/291 , F05D2250/60
摘要： An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28, or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages 74. The endwall has a hump 84 toward a pressure side of the passage and a less elevated profile toward a suction side of the passage for reducing secondary flow losses.
摘要翻译：翼型阵列包括横向延伸的端壁56，其具有从端壁突出的一系列诸如28或38的翼型件。翼型件与端壁配合以限定一系列流体流动通道74。端壁具有朝向通道的压力侧的隆起部84，并且朝向通道的吸入侧的较小的升高的轮廓减小二次流动损失。

3. 发明申请

US20070258817A1 Blade or vane with a laterally enlarged base 有权
标题翻译：刀片或叶片具有横向扩大的基座
公开(公告)号：US20070258817A1
公开(公告)日：2007-11-08
申请号：US11415892
申请日：2006-05-02
申请人： Eunice Allen-Bradley , Eric Grover , Thomas Praisner
发明人： Eunice Allen-Bradley , Eric Grover , Thomas Praisner
IPC分类号： F01D11/00
CPC分类号： F01D5/141 , F01D5/143 , F01D5/145
摘要： A blade or vane includes a platform 130 and an airfoil 132 extending from the platform. The airfoil has a pressure surface offset in a first direction D1 from a part span mean camber line 148, a suction surface offset in a second direction D2 from the part span mean camber line, and a base 146 that is laterally enlarged in the first direction for reducing secondary flow losses.
摘要翻译：叶片或叶片包括平台130和从平台延伸的翼型件132。该翼型件具有从第一方向D1到零件间距平均曲线148的压力表面偏移，从第二方向D 2偏离部分跨度平均中心线的吸力表面，以及在该第二方向上横向放大的基部146 减少二次流量损失的第一个方向。

4. 发明授权

US08511978B2 Airfoil array with an endwall depression and components of the array 有权
标题翻译：翼型阵列具有端壁凹陷和阵列的部件
公开(公告)号：US08511978B2
公开(公告)日：2013-08-20
申请号：US11415898
申请日：2006-05-02
申请人： Eunice Allen-Bradley , Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
发明人： Eunice Allen-Bradley , Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
IPC分类号： F01D1/04 , F01D9/02
CPC分类号： F01D5/145 , F01D5/143 , F01D9/041 , F05D2240/80 , F05D2250/291 , F05D2250/60
摘要： An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28 or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages 74. The endwall has a trough 100 toward a pressure side of the passage and a more elevated profile toward a suction side of the passage for reducing secondary flow losses.
摘要翻译：翼型阵列包括横向延伸的端壁56，其具有从端壁突出的一系列诸如28或38的翼型件。翼型件与端壁协作以限定一系列流体流动通道74.端壁具有朝向通道的压力侧的槽100和朝向通道的吸入侧的更加升高的型面，用于减少二次流动损失。

5. 发明授权

US08075259B2 Turbine vane airfoil with turning flow and axial/circumferential trailing edge configuration 有权
标题翻译：涡轮叶片翼型具有转向流动和轴向/周向后缘配置
公开(公告)号：US08075259B2
公开(公告)日：2011-12-13
申请号：US12371414
申请日：2009-02-13
申请人： Thomas J. Praisner , Eunice Allen-Bradley , Shankar S. Magge , Keshava B. Kumar
发明人： Thomas J. Praisner , Eunice Allen-Bradley , Shankar S. Magge , Keshava B. Kumar
IPC分类号： F01D9/00 , F01D1/02 , F03D11/00 , F03D1/04 , F03D3/04 , F03B1/04 , F03B3/16 , F04D29/44 , F04D29/54
CPC分类号： F01D9/041 , F01D5/141 , F05D2240/12 , F05D2240/122 , F05D2240/304 , F05D2250/74 , Y02T50/673
摘要： An airfoil with turning flow comprises a first surface, a second surface, a leading edge and a trailing edge. The first and second surfaces extend from the leading edge to a trailing edge. A chord extends from a midpoint of the leading edge to a midpoint of the trailing edge, defining a duct angle of at least fifteen degrees with respect to a turbine axis. An axial length of the chord defines an aspect ratio of at most one with respect to an average radial span of the leading and trailing edges. In a region of the trailing edge, an axial angle is at most four degrees and a circumferential angle is at most ten degrees, where the circumferential angle is defined in a direction opposite the turning flow.
摘要翻译：具有回转流的翼型件包括第一表面，第二表面，前缘和后缘。第一和第二表面从前缘延伸到后缘。弦从前缘的中点延伸到后缘的中点，其相对于涡轮轴线限定至少十五度的管道角度。弦的轴向长度相对于前缘和后缘的平均径向跨度限定至多一个的纵横比。在后缘的区域中，轴向角度为至多4度，圆周角度为10度以下，其中，周向角度与转向流动方向相反。

6. 发明申请

US20140037459A1 AIRFOIL DESIGN HAVING LOCALIZED SUCTION SIDE CURVATURES 有权
标题翻译： AIRFOIL设计具有本地化吸收侧曲线
公开(公告)号：US20140037459A1
公开(公告)日：2014-02-06
申请号：US13566400
申请日：2012-08-03
申请人： Andrew S. Aggarwala , Eunice Allen-Bradley , Eric A. Grover , Ricardo Trindade
发明人： Andrew S. Aggarwala , Eunice Allen-Bradley , Eric A. Grover , Ricardo Trindade
IPC分类号： F01D5/18
CPC分类号： F01D5/141 , F01D5/145 , F01D5/148 , F01D5/186 , F05D2240/124 , F05D2250/713
摘要： An airfoil for a gas turbine engine comprises a radially extending body having a transverse cross-section. The transverse cross-section comprises a leading edge, a trailing edge, a pressure side and a suction side. The pressure side extends between the leading edge and the trailing edge with a predominantly concave curvature. The suction side extends between the leading edge and the trailing edge with a predominantly convex curvature. The suction side includes an approximately flat portion flanked by forward and aft convex portions. In another embodiment, the suction side includes a series of local curvature changes that produce inflection points in the convex curvature of the suction side spaced from the trailing edge.
摘要翻译：用于燃气涡轮发动机的翼型件包括具有横截面的径向延伸体。横截面包括前缘，后缘，压力侧和吸力侧。压力侧以主要凹陷的曲率在前缘和后缘之间延伸。吸力侧以主要凸起的曲率在前缘和后缘之间延伸。吸入侧包括侧面为前后凸部的大致平坦部。在另一个实施例中，吸力侧包括一系列局部曲率变化，其产生与后缘间隔开的吸入侧的凸曲率中的拐点。

7. 发明授权

US09957801B2 Airfoil design having localized suction side curvatures 有权
公开(公告)号：US09957801B2
公开(公告)日：2018-05-01
申请号：US13566400
申请日：2012-08-03
申请人： Andrew S. Aggarwala , Eunice Allen-Bradley , Eric A. Grover , Ricardo Trindade
发明人： Andrew S. Aggarwala , Eunice Allen-Bradley , Eric A. Grover , Ricardo Trindade
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/141 , F01D5/145 , F01D5/148 , F01D5/186 , F05D2240/124 , F05D2250/713
摘要： An airfoil for a gas turbine engine comprises a radially extending body having a transverse cross-section. The transverse cross-section comprises a leading edge, a trailing edge, a pressure side and a suction side. The pressure side extends between the leading edge and the trailing edge with a predominantly concave curvature. The suction side extends between the leading edge and the trailing edge with a predominantly convex curvature. The suction side includes an approximately flat portion flanked by forward and aft convex portions. In another embodiment, the suction side includes a series of local curvature changes that produce inflection points in the convex curvature of the suction side spaced from the trailing edge.

8. 发明授权

US09133713B2 Gas turbine engine turbine blade airfoil profile 有权
标题翻译：燃气轮机发动机涡轮叶片翼型
公开(公告)号：US09133713B2
公开(公告)日：2015-09-15
申请号：US13539701
申请日：2012-07-02
申请人： Eunice Allen-Bradley
发明人： Eunice Allen-Bradley
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2250/74 , Y02T50/672 , Y02T50/673
摘要： A turbine blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
摘要翻译：用于燃气涡轮发动机的涡轮叶片包括翼型件，其包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供从平台沿径向方向延伸到尖端的外部翼型表面。外部翼面表面基本上符合由表1中所示的一组笛卡尔坐标所描述的翼型的多个横截面轮廓。笛卡尔坐标由通过局部轴向弦缩放的轴向坐标提供。圆周坐标由局部轴向弦和跨度位置缩放。局部轴向弦对应于跨距处的前缘和后缘之间的翼型的宽度。

9. 发明授权

US08517686B2 Flow passage for gas turbine engine 有权
标题翻译：燃气轮机发动机流道
公开(公告)号：US08517686B2
公开(公告)日：2013-08-27
申请号：US12623051
申请日：2009-11-20
申请人： Eunice Allen-Bradley , Thomas J. Praisner , Eric A. Grover
发明人： Eunice Allen-Bradley , Thomas J. Praisner , Eric A. Grover
IPC分类号： F01D5/30
CPC分类号： F01D9/041 , F01D5/143 , F01D5/145 , F04D29/324 , F04D29/681 , F05D2270/17 , Y02T50/673
摘要： Inefficiencies associated with the formation of horseshoe vortices in a gas turbine engine having a row of radially extending airfoils, are mitigated with an improved flow passage defined by the suction and pressure surface of two adjacent airfoils and endwalls (disposed proximal to the radially inner and outer ends of the airfoils). The flow passage includes a ridge disposed in one of the endwalls adjacent a suction surface of one of the airfoils, the ridge extending longitudinally from a location at or near the maximum circumferential extent of the airfoil suction side to a downstream location proximal to the trailing edge of the suction surface.
摘要翻译：在具有一排径向延伸的翼型的燃气涡轮发动机中形成马蹄形涡流的低效率被改进的流动通道所限定，该流动通道由两个相邻翼型件和端壁的吸入和压力表面限定（靠近径向内部和外侧机翼末端）。流动通道包括设置在邻近翼型中的一个的吸力表面的一个端壁中的脊部，脊部从翼型件吸入侧的最大圆周范围处或附近的位置纵向延伸到靠近后缘的下游位置的吸力表面。

10. 发明授权

US08366399B2 Blade or vane with a laterally enlarged base 有权
标题翻译：刀片或叶片具有横向扩大的基座
公开(公告)号：US08366399B2
公开(公告)日：2013-02-05
申请号：US11415892
申请日：2006-05-02
申请人： Eunice Allen-Bradley , Eric A. Grover , Thomas J. Praisner
发明人： Eunice Allen-Bradley , Eric A. Grover , Thomas J. Praisner
IPC分类号： F04D29/38 , F04D29/00
CPC分类号： F01D5/141 , F01D5/143 , F01D5/145
摘要： A blade or vane includes a platform 130 and an airfoil 132 extending from the platform. The airfoil has a pressure surface offset in a first direction D1 from a part span mean camber line 148, a suction surface offset in a second direction D2 from the part span mean camber line, and a base 146 that is laterally enlarged in the first direction for reducing secondary flow losses.
摘要翻译：叶片或叶片包括平台130和从平台延伸的翼型件132。翼型件具有从零件跨度平均弯度线148的第一方向D1的压力表面偏移，在距第二方向D2偏离部分跨度平均弯度线的吸力表面，以及在第一方向上横向放大的基部146 用于减少二次流量损失。

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