Compatibility of Transonic Flows at Thick Trailing Edge in Turbine Blade Row

Abstract

In transonic turbine blades with thick trailing edge, the base pressure strongly influences the cascade performances. This paper presents two methods for predicting the base pressure, which are extension of the analyses on the backward facing step by Korst (neglecting upstream boundary layer) and McDonald (taking account of upstream boundary layer). The compatibility is considered between separated flows (jets) from suction and pressure surfaces in each method. The validity of both methods are discussed in comparison with the experiment of a two-dimensional turbine cascade with high stagger.