公开(公告)号：US20190120059A1

公开(公告)日：2019-04-25

申请号：US15793454

申请日：2017-10-25

Applicant: United Technologies Corporation

Inventor： Timothy Charles Nash ,  Loubriel Ramirez

IPC: F01D5/14

CPC classification number: F01D5/145 ,  F01D5/143 ,  F01D9/041 ,  F04D29/522 ,  F04D29/68 ,  F05D2240/12

Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extends along an axially chord between a leading edge and a trailing edge. A first profiled region is recessed into the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil. A third profiled region is recessed into the endwall along adjacent the leading edge of the second side of the second airfoil. The third profiled region is at least partially axially aligned with the second profiled region.

公开(公告)号：US20200318484A1

公开(公告)日：2020-10-08

申请号：US16378161

申请日：2019-04-08

Applicant: United Technologies Corporation

Inventor： Loubriel Ramirez

IPC: F01D5/14

Abstract: A turbine section includes a pair of adjacent turbine airfoils and an endwall extending between the airfoils. The endwall includes a first feature spanning approximately twenty percent pitch and having a first depression with a first maximum depression located between twenty percent and sixty percent of an axial chord length of the first airfoil, a second feature adjacent the first feature with the second feature spanning approximately forty percent pitch and having a first peak with a maximum height located between twenty percent and sixty percent of the axial chord length of the first airfoil, and a third feature adjacent the second feature and first side of the second airfoil with the third feature spanning approximately forty percent pitch and having a second depression with a second maximum depression located between thirty percent and sixty percent of an axial chord length of the second airfoil.

公开(公告)号：US20200318483A1

公开(公告)日：2020-10-08

申请号：US16378122

申请日：2019-04-08

Applicant: United Technologies Corporation

Inventor： Loubriel Ramirez

IPC: F01D5/02 ,  F01D9/04

Abstract: A turbine section includes a pair of adjacent turbine airfoils and an endwall extending between the airfoils. The endwall includes a first feature spanning approximately thirty percent pitch and having a first depression with a maximum depression located between twenty percent and eighty percent of the axial chord length of the first airfoil, a second feature spanning approximately thirty percent pitch and having a first peak with a maximum height located between sixty percent and ninety percent of the axial chord length of the first airfoil, and a third feature spanning approximately thirty percent pitch and having a second depression with a maximum depression located between twenty percent and fifty percent of the axial chord length of the second airfoil.

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：US10968748B2

公开(公告)日：2021-04-06

申请号：US16378122

申请日：2019-04-08

Applicant: United Technologies Corporation

Inventor： Loubriel Ramirez

IPC: F01D5/14

Abstract: A turbine section includes a pair of adjacent turbine airfoils and an endwall extending between the airfoils. The endwall includes a first feature spanning approximately thirty percent pitch and having a first depression with a maximum depression located between twenty percent and eighty percent of the axial chord length of the first airfoil, a second feature spanning approximately thirty percent pitch and having a first peak with a maximum height located between sixty percent and ninety percent of the axial chord length of the first airfoil, and a third feature spanning approximately thirty percent pitch and having a second depression with a maximum depression located between twenty percent and fifty percent of the axial chord length of the second airfoil.

公开(公告)号：US10508550B2

公开(公告)日：2019-12-17

申请号：US15793454

申请日：2017-10-25

Applicant: United Technologies Corporation

Inventor： Timothy Charles Nash ,  Loubriel Ramirez

IPC: F01D5/14 ,  F04D29/68 ,  F04D29/52 ,  F01D9/04

Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extends along an axially chord between a leading edge and a trailing edge. A first profiled region is recessed into the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil. A third profiled region is recessed into the endwall along adjacent the leading edge of the second side of the second airfoil. The third profiled region is at least partially axially aligned with the second profiled region.

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， 。