公开(公告)号：US10012086B2

公开(公告)日：2018-07-03

申请号：US15034429

申请日：2014-11-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David M. Pons ,  Loubriel Ramirez

IPC: F02C3/04 ,  F01D5/14 ,  F01D9/04 ,  F01D9/02

CPC classification number: F01D5/141 ,  F01D9/02 ,  F01D9/041 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2250/711 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673

Abstract: An example airfoil includes an airfoil body with a leading edge and a trailing edge joined by a pressure side and a suction 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).

公开(公告)号：US20200248574A1

公开(公告)日：2020-08-06

申请号：US16267955

申请日：2019-02-05

Applicant: United Technologies Corporation

Inventor： Angela C. Reisch ,  Carson A. Roy Thill ,  Dairus Deylan McDowell ,  Jin Hu ,  Jeremy Drake ,  Gregory A. O'Connor ,  David M. Pons ,  Katelyn Kwoka

IPC: F01D9/04 ,  F01D9/02

Abstract: An on-board injector for delivering discharge air toward a turbine rotor of a gas turbine engine. The on-board injector having: a first wall; a second wall spaced from said first wall to define an annular inlet and an annular exit, wherein the first wall has a first length and the second wall has a second length; and a plurality of airfoils extending between the first wall and the second wall to segregate discharge air from the annular inlet, wherein each of the plurality of airfoils extend from the annular inlet and the annular exit and completely across the first length and the second length.

公开(公告)号：US20160281509A1

公开(公告)日：2016-09-29

申请号：US15034429

申请日：2014-11-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David M. Pons ,  Loubriel Ramirez

IPC: F01D5/14 ,  F01D9/02 ,  F02C3/04

CPC classification number: F01D5/141 ,  F01D9/02 ,  F01D9/041 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2250/711 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673

Abstract: An example airfoil includes an airfoil body with a leading edge and a trailing edge joined by a pressure side and a suction 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).

Abstract translation: 示例性翼型件包括具有前缘的翼型件主体和通过压力侧和吸力侧连接的后缘，以提供从至少一个平台沿径向方向延伸的外部翼型件表面。 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。 局部轴向弦对应于在跨距位置的前缘和后缘之间的翼型的宽度，并且表1中的笛卡尔坐标具有相对于高达+0.050英寸（+1.27mm）的指定坐标的公差， 。