The paper considers the processes of design and validation of gas turbine engine cooling elements of the high pressure turbine that apply the prediction methodology of conjugate heat transfer and validation of the experimental measurements correspondence. To get the blade body temperatures corresponding to the measured ones, the correctable film cooling temperatures as well as gas and air parameters are set. The predicted temperatures of metal are compared with ones measured during the gas turbine engine test in order to substantiate the presented procedure and adjust the gas temperature at the inlet to the gas domain.
Conjugate Heat Transfer Validation of Gas Turbine Engine Cooling Turbine Vanes
Russ. Aeronaut.
Russian Aeronautics ; 66 , 2 ; 316-324
01.04.2023
9 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Cooling Modern Aero Engine Turbine Blades and Vanes
SAE Technical Papers | 1966
|Air Cooling of Turbine Blades and Vanes
Emerald Group Publishing | 1967
|