가스터빈 엔진 터빈 블레이드의 냉각성능 상사시험 평가 연구

Abstract

In this study, a similarity test was designed to evaluate the cooling performance of the high-pressure turbine blades of a gas turbine engine, and a study was conducted to verify the similarity through analysis and experiments. The main similarity variables representing the cooling performance of the turbine blades were defined, and the similarity test conditions were derived from the engine conditions so that the similarity variables could satisfy the similarity. It was confirmed that the similarity was satisfied by performing a conjugated heat transfer analysis on the same test conditions, and the cooling performance of the turbine blades was experimentally evaluated by conducting a heat transfer experiment using an infrared thermal imaging camera under the same conditions. In conclusion, it was confirmed that the cooling performance of high-temperature components such as high-pressure turbine nozzles and blades operating at high temperatures in a relaxed pressure and temperature environment without simulating a high-pressure and high-temperature environment such as an engine can be evaluated through a similar test.