公开(公告)号：US09790796B2

公开(公告)日：2017-10-17

申请号：US14031206

申请日：2013-09-19

Applicant: General Electric Company

Inventor： John David Stampfli ,  Ajay Keshava Rao ,  Rudolf Konrad Selmeier

IPC: F01D5/14

CPC classification number: F01D5/14 ,  F01D5/141 ,  F05D2250/712 ,  F05D2250/713

Abstract: An airfoil is disclosed herein. The airfoil may include a leading edge, a trailing edge, a suction side defined between the leading edge and the trailing edge, and a pressure side defined between the leading edge and the trailing edge opposite the suction side. The pressure side may include a concave profile about the trailing edge that varies from a profile of a remainder of the pressure side.

公开(公告)号：US20160153465A1

公开(公告)日：2016-06-02

申请号：US14556452

申请日：2014-12-01

Applicant: General Electric Company

Inventor： Sungho Yoon ,  John David Stampfli ,  Ramakrishna Venkata Mallina ,  Vittorio Michelassi ,  Giridhar Jothiprasad ,  Ajay Keshava Rao ,  Rudolf Konrad Selmeier ,  Davide Giacché ,  Ivan Malcevic

IPC: F04D29/52 ,  F02C3/04 ,  F01D11/08

CPC classification number: F04D29/526 ,  F04D29/321 ,  F04D29/522 ,  F04D29/685

Abstract: An axial compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow in the compressor. The one or more endwall treatments having a height formed in an interior surface of a compressor casing or a compressor hub and configured to return a flow adjacent a plurality of rotor blade tips or a plurality of stator blade tips to a cylindrical flow passage upstream of a point of removal of the flow. Each of the endwall treatments defining a front wall, a rear wall, an outer wall extending between the front wall and the rear wall, an axial overhang, an axial overlap, an axial lean angle and a tangential lean angle. The axial overhang extending upstream to overhang at least one of the at least one set of rotor blades or the at least one set of stator blades. The axial overlap extending downstream to overlap at least one of the at least one set of rotor blades or the at least one set of stator blades.

Abstract translation: 一种用于燃气涡轮发动机的轴向压缩机，包括用于控制压缩机中的泄漏流的一个或多个端壁处理。 所述一个或多个端壁处理具有形成在压缩机壳体或压缩机毂的内表面中的高度，并且被配置为将邻近多个转子叶片尖端或多个定子叶片尖端的流返回到一个圆柱形流动通道 清除流量点。 每个端壁处理限定了前壁，后壁，在前壁和后壁之间延伸的外壁，轴向突出，轴向重叠，轴向倾斜角和切向倾斜角。 所述轴向突出部在所述至少一组所述转子叶片或所述至少一组定子叶片中的至少一个的上游延伸。 在下游延伸的轴向重叠与所述至少一组转子叶片或至少一组定子叶片中的至少一个重叠。

公开(公告)号：US20140130513A1

公开(公告)日：2014-05-15

申请号：US13673117

申请日：2012-11-09

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ya-tien Chiu ,  John David Stampfli ,  Rudolf Selmeier

IPC: F02C3/06 ,  F04D19/00 ,  F04D27/00

CPC classification number: F02C3/06 ,  F01D17/162 ,  F04D19/00 ,  F04D21/00 ,  F04D27/002 ,  F04D27/0246 ,  F05D2260/15

Abstract: A compressor section of a gas turbine generally includes a stage of inlet guide vanes positioned adjacent to an inlet of the compressor section and a stage of rotor blades disposed downstream from the inlet guide vanes. A stage of stator vanes is positioned downstream from the stage of rotor blades. The stage of stator blades includes a row of leading guide vanes having a trailing edge. A row of trailing guide vanes coupled to an actuator is disposed between two corresponding adjacent leading guide vanes. Each of the trailing guide vanes includes a trailing edge. The leading edge of each trailing guide vane is disposed upstream of the trailing edge of a corresponding leading guide vane when the trailing guide vane is in an open position and downstream from the trailing edge of the corresponding leading guide vane when the trailing guide vane is in a closed position.

Abstract translation: 燃气涡轮机的压缩机部分通常包括邻近压缩机部分的入口设置的入口引导叶片的台和设置在入口导叶的下游的转子叶片的台。 定子叶片的一级位于转子叶片的下游。 定子叶片的阶段包括一排具有后缘的导向导叶。 连接到致动器的一排尾导叶设置在两个对应的相邻的导向叶片之间。 每个拖尾导叶包括后缘。 当拖尾导叶处于打开位置并且当牵引导叶处于相对应的导向叶片的后缘的下游时，每个拖尾导叶的前缘设置在对应的导向叶片的后缘的上游 关闭位置