公开(公告)号：WO2014042720A3

公开(公告)日：2014-05-30

申请号：PCT/US2013044453

申请日：2013-06-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ALLEN-BRADLEY EUNICE

IPC: F01D5/14 ,  F01D5/12 ,  F02C7/00

CPC classification number: F01D5/141 ,  F05D2250/74 ,  Y02T50/672 ,  Y02T50/673

Abstract: 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.

Abstract translation: 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。

公开(公告)号：WO2014074190A3

公开(公告)日：2014-07-17

申请号：PCT/US2013054944

申请日：2013-08-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PRAISNER THOMAS J ,  AGGARWALA ANDREW S ,  NASH TIMOTHY CHARLES ,  ALLEN-BRADLEY EUNICE ,  GROVER ERIC A

IPC: F01D1/04 ,  F01D5/02 ,  F01D5/22 ,  F04D29/44

CPC classification number: F01D9/02 ,  F01D5/143 ,  F01D5/145 ,  F04D29/324 ,  F04D29/542 ,  F04D29/681 ,  Y02T50/673

Abstract: 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.

Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。 每个翼型件可以具有在前缘和后缘之间以弦状轴向延伸的第一侧和相对的第二侧。 翼型件可以在端壁上周向间隔开，从而在相邻翼型之间限定多个流动通道。 翼型阵列还可以包括凸出的轮廓区域，该凸形轮廓区域从靠近所述多个翼型件中的至少一个的前缘的所述多个翼型件中的至少一个的第一侧面的端壁延伸，并且在所述多个翼型件中的凹形轮廓区域 并且延伸穿过所述多个流动通道中的所述至少一个。

公开(公告)号：EP2900920A4

公开(公告)日：2016-07-06

申请号：EP13853442

申请日：2013-08-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PRAISNER THOMAS J ,  AGGARWALA ANDREW S ,  NASH TIMOTHY CHARLES ,  ALLEN-BRADLEY EUNICE ,  GROVER ERIC A

IPC: F01D5/14 ,  F04D29/68

CPC classification number: F01D9/02 ,  F01D5/143 ,  F01D5/145 ,  F04D29/324 ,  F04D29/542 ,  F04D29/681 ,  Y02T50/673

公开(公告)号：EP2880280A4

公开(公告)日：2016-07-13

申请号：EP13826145

申请日：2013-08-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AGGARWALA ANDREW S ,  ALLEN-BRADLEY EUNICE ,  GROVER ERIC A ,  TRINDADE RICARDO

IPC: F02C7/00 ,  F01D5/14

CPC classification number: F01D5/186 ,  F01D5/141 ,  F01D5/145 ,  F01D5/148 ,  F05D2240/124 ,  F05D2250/713

Abstract: 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.

Abstract translation: 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的主体。 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，吸入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。