公开(公告)号：US20220170375A1

公开(公告)日：2022-06-02

申请号：US17433985

申请日：2020-12-15

Applicant: DALIAN UNIVERSITY OF TECHNOLOGY

Inventor： Dong LV ,  Nan WANG ,  Xiaofang WANG ,  Xingao KONG ,  Yinan SUN

IPC: F01D5/18

Abstract: The present invention belongs to the technical field of turbine cooling of aero-engine and gas turbine, and relates to the honeycomb-like helically cavity cooling structure of turbine blade. The honeycomb-like helically cavity cooling structure of turbine blade includes hollow turbine blade, honeycomb-like helically cavity and pin fins. Some cooling channels are arranged inside the hollow the hollow turbine blade, the cooling gas flows through the tunnels and cools the blade. Multi-arrays of honeycomb-like helically cavity are arranged in the blade wall, for cooling gas to enter and convective cooling. A cylindrical pin fin is arranged in the center of the honeycomb-like helically cavity. In each unit, the inlet hole and film hole are located on both sides of the blade wall, and the center lines of them are parallel in the same vertical plane.