A Gas Turbine Test Facility of Blade Aerothermal Performance

With the increasing demands of gas turbines performance and aero-engines performance in industry, it’s urgent to develop the advanced gas turbines with higher efficient, longer operation life, lower emissions and larger thrust-to-weight ratio. Due to the complicated and three-dimensional (3D) flow field in blade passage, acquiring accurate and reliable results are difficult by numerical simulations and theoretical analysis, so it’s necessary to carry out experiment research. This paper presents a novel gas turbine test facility of blade aerothermal performance, which can provide transient step rise of mainstream temperature and carry out flow, heat transfer and film cooling studies at different incidence angles, different pitch cascades and different types cascades (vane and blade) by Infrared measurement technology. To achieve the goal of rapidity and ease build, the test section is modularly designed and constructed. In addition, the optical ports are designed to provide visualization measurements and Infrared temperature measurements. The wall temperature is measured by Infrared technology and the heat transfer and film cooling performance are investigated by the data reduction of Dual Linear Regression Technique (DLRT). Simultaneously, the benchmark aerodynamic measurements were carried out and the results indicate the design goals are acquired and transient switching between bypass line and test line can be performed. © 2023 Science Press. All rights reserved.