机译:Heat transfer in a trailing cooling channel using ejection slot with different chordwise length ratio of impingement cavity
National Key Laboratory of Science and Technology on Aero-engine Aero-thermodynamics, School of Energy and Power Engineering, Beihang University;
BeiJing Aerospace Propulsion Institute;
Avic Commercial Aircraft Engine Co., Ltd;
Turbine blade cooling; Trailing edge channel; Lateral ejection; Heat transfer; Impingement cooling;