Unsteady Wake Effect on Film Temperature and Effectiveness Distributions for a Gas Turbine Blade Conference Paper uri icon

abstract

  • The film effectiveness and coolant jet temperature profile on the suction side of a gas turbine blade were measured using a transient liquid crystal and a cold-wire technique, respectively. The blade has only one row of film holes near the gill hole portion on the suction side of the blade. Tests were performed on a five-blade linear cascade in a low-speed wind tunnel. The mainstream Reynolds number based on cascade exit velocity was 5.3105. Upstream unsteady wakes were simulated using a spoke-wheel type wake generator. Coolant blowing ratio was varied from 0.6 to 1.2. Wake Strouhal number was kept at 0 and 0.1. Results show that unsteady wake reduces film cooling effectiveness. Results also show that film injection enhances local heat transfer coefficient while the unsteady wake promotes earlier boundary-layer transition. The development of coolant jet temperature profiles could be used to explain the film cooling performance. [S0889-504X(00)00402-5]

published proceedings

  • Journal of Turbomachinery

author list (cited authors)

  • Teng, S., Sohn, D. K., & Han, J.

citation count

  • 34

complete list of authors

  • Teng, Shuye||Sohn, Dong Kee||Han, Je-Chin

publication date

  • February 1999