Анализ использования профилированных отверстий перфорации для повышения качества пленочного охлаждения спинки сопловых лопаток турбин

Aleksey Sergeevich Tihonov; Nikolay Yurevich Samohvalov

Analysis of using shaped cooling holes to improve the quality of film cooling on the suction side of turbine nozzle guide vanes

Authors

Aleksey Sergeevich Tihonov
Nikolay Yurevich Samohvalov

Keywords:

high pres sure turbine; nozzle guide vane; thermal state; numerical modeling; shaped cooling holes.

Abstract

Numerical modeling of the thermal state of 1st stage turbine nozzle guide vane of modern gas-turbine engine in CHT formulation in ANSYS CFX 13.0 is done. The analysis of the thermal state of the basic design of the blade and influence of using of the fan-shaped cooling holes on cooling effectiveness and thermal state of the suction side is done. Using of the fan-shaped cooling holes allowed to reduce temperature of the suction side of nozzle guide vane on 25...30 C.