公开(公告)号：US20240254883A1

公开(公告)日：2024-08-01

申请号：US18161122

申请日：2023-01-30

Applicant: General Electric Company

Inventor： Kishore Ramakrishnan ,  Nikolai N. Pastouchenko ,  Trevor Howard Wood ,  Thomas William Vandeputte

IPC: F01D5/14

CPC classification number: F01D5/142 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2250/713 ,  F05D2260/96

Abstract: A turbine airfoil is provided. The turbine airfoil defines a chord line, a spanwise direction, a span along the spanwise direction, and a midpoint along the spanwise direction. The turbine airfoil includes a pressure side and a suction side. The pressure side and the suction side intersecting at a leading edge and a trailing edge. The turbine airfoil further includes a root and a tip at opposing ends along the spanwise direction. In addition, the turbine airfoil defines a leading edge reference line extending from where the leading edge meets the root to where the leading edge meets the tip and a trailing edge reference line extending from where the trailing edge meets the root to where the trailing edge meets the tip. The turbine airfoil includes a lobe positioned at the leading edge or the trailing edge and defines a maximum axially height relative to the leading edge reference line or the trailing edge reference line. The maximum axial height being equal to at least five percent of the chord line of the turbine airfoil.

公开(公告)号：US11952912B2

公开(公告)日：2024-04-09

申请号：US17894307

申请日：2022-08-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Thomas William Vandeputte ,  Paul Hadley Vitt ,  Daniel Endecott Osgood ,  Brian David Keith

IPC: F01D5/18 ,  F02C7/12

CPC classification number: F01D5/18 ,  F02C7/12 ,  F05D2260/20

Abstract: A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.

公开(公告)号：US20180023397A1

公开(公告)日：2018-01-25

申请号：US15217012

申请日：2016-07-22

Applicant: General Electric Company

Inventor： Thomas William Vandeputte

IPC: F01D5/14 ,  B33Y10/00 ,  B29C67/00 ,  B33Y80/00 ,  B23K26/342 ,  B23K26/70 ,  F01D9/04 ,  B33Y50/02

CPC classification number: F01D5/145 ,  B23K15/0086 ,  B23K15/0093 ,  B23K26/342 ,  B23K2101/001 ,  B23K2103/26 ,  B29L2031/08 ,  B33Y50/02 ,  B33Y80/00 ,  F01D5/141 ,  F01D5/147 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/61 ,  F05D2260/204 ,  F05D2260/22141 ,  Y02T50/673 ,  Y02T50/676

Abstract: A blade includes an airfoil body defined by a concave pressure side outer wall and a convex suction side outer wall that connect along a leading edge and a trailing edge. The blade also includes a first corrugated surface extending from the trailing edge to the leading edge on an outer surface of the concave pressure side outer wall, and/or a second corrugated surface extending from the trailing edge to the leading edge on an outer surface of the convex suction side outer wall. The blade acts to reduce flow velocity losses associated with wake mixing by accelerating the mixing process from the source of the wake to minimize inflated unsteady mixing that occurs within a downstream blade row.

公开(公告)号：US20160146038A1

公开(公告)日：2016-05-26

申请号：US14550506

申请日：2014-11-21

Applicant: General Electric Company

Inventor： Thomas William Vandeputte

IPC: F01D17/16 ,  F01D9/04

CPC classification number: F01D17/162 ,  F01D5/145 ,  F01D9/045 ,  F05D2240/125

Abstract: A vane for a turbomachine includes a pressure surface and a suction surface opposite the pressure surface. The pressure surface and the suction surface define a width therebetween. The vane also includes a first end. The first end includes a distal portion, a proximal portion, a pressure surface first portion, and a suction surface first portion. At least one of the pressure surface first portion and the suction surface first portion slope away from the other of the pressure surface first portion and the suction surface first portion such that the width increases from a first end minimum width at the proximal portion to a first end maximum width at the distal portion.

Abstract translation: 用于涡轮机的叶片包括压力表面和与压力表面相对的吸力表面。 压力表面和吸力表面之间限定了宽度。 叶片还包括第一端。 第一端包括远端部分，近端部分，压力表面第一部分和吸力表面第一部分。 所述压力表面第一部分和所述吸力表面第一部分中的至少一个从所述压力表面第一部分和所述吸力表面第一部分中的另一个部分倾斜，使得所述宽度从所述近端部分处的第一端部最小宽度增加到第一部分 在远端部分的最终最大宽度。