公开(公告)号：US09506347B2

公开(公告)日：2016-11-29

申请号：US13720640

申请日：2012-12-19

Applicant: Solar Turbines Incorporated

Inventor： Jeremiah W. Key

IPC: F01D5/14

CPC classification number: F01D5/141 ,  Y02T50/671 ,  Y02T50/673

Abstract: A compressor blade for a gas turbine engine includes a root configured to engage a hub of the gas turbine engine, and an airfoil radially extending a distance from the root to a tip. The airfoil includes a suction side, a pressure side, a leading edge connecting the suction and pressure sides, and a trailing edge connecting the suction and pressure sides opposite the leading edge. The distance that the airfoil extends from the root to the tip may be divided into a plurality of radially adjacent regions. At least one, but not all, of the plurality of radially adjacent regions may have a substantially constant thickness.

Abstract translation: 用于燃气涡轮发动机的压缩机叶片包括构造成接合燃气涡轮发动机的轮毂的根部和从根部到尖端径向延伸一定距离的翼型件。 翼型件包括吸入侧，压力侧，连接吸力侧和压力侧的前缘以及连接与前缘相对的吸力侧和压力侧的后缘。 翼型件从根部延伸到尖端的距离可以被分成多个径向相邻的区域。 多个径向相邻区域中的至少一个但不是全部可以具有基本恒定的厚度。