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1. 发明申请

WO2014028421A1 GAS TURBINE ENGINE AIRFOIL PROFILE 审中-公开
标题翻译：气体涡轮发动机气翼型材
公开(公告)号：WO2014028421A1
公开(公告)日：2014-02-20
申请号：PCT/US2013/054616
申请日：2013-08-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ALLEN-BRADLEY, Eunice
IPC分类号： F02C7/00 , F01D5/00
CPC分类号： F01D5/14 , F01D5/141 , F05D2250/74 , Y02T50/672 , Y02T50/673 , Y10S416/05
摘要： An airfoil for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body including a leading edge and a trailing edge joined by a pressure side and a suction side spaced apart from the pressure side to provide an external airfoil surface extending in a radial direction from at least one platform. 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 scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location, and the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to ±0.050 inches (±1.27 mm).
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的翼型件尤其包括：机翼本体，其包括通过压力侧连接的前缘和后缘以及与压力侧间隔开的吸力侧，以提供从至少一个平台沿径向方向延伸的外部翼型表面。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。笛卡尔坐标由轴向坐标提供，该坐标由局部轴向弦，圆周坐标通过局部轴向和弦和跨度位置进行缩放。局部轴向弦对应于跨距位置处的前缘和后缘之间的翼型的宽度，表1中的笛卡尔坐标具有相对于指定坐标的公差高达±0.050英寸（±1.27mm）。

2. 发明申请

WO2014074190A2 ENDWALL CONTOURING 审中-公开
公开(公告)号：WO2014074190A2
公开(公告)日：2014-05-15
申请号：PCT/US2013/054944
申请日：2013-08-14
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： PRAISNER, Thomas, J. , AGGARWALA, Andrew, S. , NASH, Timothy, Charles , ALLEN-BRADLEY, Eunice , GROVER, Eric, A.
IPC分类号： F01D5/14 , F01D9/02
CPC分类号： F01D9/02 , F01D5/143 , F01D5/145 , F04D29/324 , F04D29/542 , F04D29/681 , Y02T50/673
摘要： An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages.
摘要翻译：公开了一种翼型阵列。翼型阵列可以包括端壁，以及从端壁径向突出的多个翼型件。每个翼型可以具有在前缘和后缘之间沿弦轴向延伸的第一侧和相对的第二侧。翼型件可以在端壁上沿圆周间隔开，从而在相邻翼型件之间限定多个流动通道。翼型阵列可进一步包括从靠近所述多个翼型中的至少一个的前缘附近的所述多个翼型中的至少一个翼型的第一侧的端壁延伸的凸形轮廓区域以及位于所述翼型中的凹形轮廓区域端壁并延伸跨过所述多个流动通道中的所述至少一个。

3. 发明申请

WO2014022762A1 AIRFOIL DESIGN HAVING LOCALIZED SUCTION SIDE CURVATURES 审中-公开
标题翻译： AIRFOIL设计具有本地化吸收侧曲线
公开(公告)号：WO2014022762A1
公开(公告)日：2014-02-06
申请号：PCT/US2013/053399
申请日：2013-08-02
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： AGGARWALA, Andrew S. , ALLEN-BRADLEY, Eunice , GROVER, Eric A. , TRINDADE, Ricardo
IPC分类号： F02C7/00 , F01D5/00
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。吸入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。

4. 发明申请

WO2014042720A2 GAS TURBINE ENGINE TURBINE BLADE AIRFOIL PROFILE 审中-公开
标题翻译：燃气涡轮发动机涡轮叶片翼型
公开(公告)号：WO2014042720A2
公开(公告)日：2014-03-20
申请号：PCT/US2013/044453
申请日：2013-06-06
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ALLEN-BRADLEY, Eunice
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机叶片包括翼型件，该翼型件包括由间隔开的压力侧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至翼尖的外翼型表面。外部翼型表面基本上与由表1中列出的一组笛卡尔坐标描述的翼型的多个横截面轮廓形成。笛卡尔坐标由通过局部轴向弦伸缩的轴向坐标提供。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度位置处的前缘和后缘之间的翼型的宽度。

5. 发明公开

EP2880280A1 AIRFOIL DESIGN HAVING LOCALIZED SUCTION SIDE CURVATURES 有权转让
标题翻译：新浪拥有多家地区SIDESAUGKRÜMMUNGEN涡轮叶片造型
公开(公告)号：EP2880280A1
公开(公告)日：2015-06-10
申请号：EP13826145.8
申请日：2013-08-02
申请人： United Technologies Corporation
发明人： AGGARWALA, Andrew S. , ALLEN-BRADLEY, Eunice , GROVER, Eric A. , TRINDADE, Ricardo
IPC分类号： F02C7/00 , F01D5/00
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.

6. 发明公开

EP2900920A2 ENDWALL CONTOURING 有权转让
标题翻译：端壁轮廓
公开(公告)号：EP2900920A2
公开(公告)日：2015-08-05
申请号：EP13853442.5
申请日：2013-08-14
申请人： United Technologies Corporation
发明人： PRAISNER, Thomas, J. , AGGARWALA, Andrew, S. , NASH, Timothy, Charles , ALLEN-BRADLEY, Eunice , GROVER, Eric, A.
IPC分类号： F01D1/04 , F01D5/02 , F01D5/22 , F04D29/44
CPC分类号： F01D9/02 , F01D5/143 , F01D5/145 , F04D29/324 , F04D29/542 , F04D29/681 , Y02T50/673
摘要： An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages.

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