公开(公告)号：WO2014092833A3

公开(公告)日：2014-08-14

申请号：PCT/US2013061123

申请日：2013-09-23

Applicant: UNITED TECHNOLOGIES CORP ,  CHUANG SUE-LI ,  DONG YUAN ,  HINGORANI SANJAY S ,  PRASAD DILIP

Inventor： CHUANG SUE-LI ,  DONG YUAN ,  HINGORANI SANJAY S ,  PRASAD DILIP

IPC: F01D5/14 ,  F01D5/12 ,  F02C7/00

CPC classification number: F04D29/384 ,  F01D5/141 ,  F05D2220/36 ,  F05D2250/74 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T137/0536 ,  Y10T137/0645

Abstract: A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends 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 the 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风扇叶片包括翼型，所述翼型包括由压力侧和吸力侧连接的前缘和后缘，以提供沿径向方向延伸至尖端的外部翼型表面。 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。

公开(公告)号：EP3126638A4

公开(公告)日：2017-04-12

申请号：EP15774355

申请日：2015-03-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BILLINGS SCOTT C ,  GOTTSCHALK MICHAEL K ,  OWEN WILLIAM D ,  GALLAGHER EDWARD J ,  WHITLOW DARRYL ,  CHUANG SUE-LI ,  SADEGHI MANI

IPC: F01D5/14

CPC classification number: F04D29/384 ,  F01D5/141 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/35 ,  F05D2250/70 ,  Y02T50/672 ,  Y02T50/673

Abstract: In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.