Year: 2025
Type: conference-paper
Abstract: Increasing turbine inlet temperature is an important way to improve gas turbine performance and thermal efficiency, the cooling problem has become one of the key technologies to be solved in the research and development of high performance turbines. In this paper, the research status of inner channel cooling, film cooling and perspiration cooling of turbine blades are introduced. The internal cooling channels should complement the multi-channel research under rotating conditions, and the film cooling technology should pay attention to the balance between new film performance and easy application, the mechanism of transpiration cooling should be further studied by means of numerical simulation and experimental verification.
Author: Zuopeng Zhou
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: gold
OpenAlex ID: W4414307327