In modern gas turbine, the over tip leakage flow is inevitably generated in the tip gap of the
first stage turbine blade due to the freestanding airfoil. In order to obtain a higher thermal …

At three tip gap sizes, two kinds of cooling-hole distributions and three blowing ratios, heat
transfer coefficient and adiabatic film cooling effectiveness on a blade squealer tip with …

Numerical investigations of heat transfer and film cooling effect on the conventional squealer
tip, no PS rim squealer tip and PS winglet squealer tip have been performed at three …

The heat transfer characteristics and aerodynamic performance of three different squealer
winglet structures based on GE-E3 turbine rotor squealer tip are numerically investigated …

To investigate the effects of tip gap height and the squealer cavity depth on aerothermal
performance of a gas turbine rotor, two tip gap height and eight squealer cavity depth are …

A rib-slot blade tip is proposed to improve the film cooling performance of an unshrouded
gas turbine blade tip in the current paper. The rib-slot blade tip is formed by arranging the …

The squealer tip is acknowledged as an effective and dependable design for minimizing
leakage loss and reducing thermal load in high-pressure turbine blades. After confirming the …

An experimental investigation is performed to study the effect of film-hole configurations on
the blade tip film cooling performance in a five-blade linear cascade. Six film-hole …

Numerical investigations have been performed to investigate the heat transfer characteristic
on the squealer–winglet tip, which is also compared with the conventional squealer tip and …

Heat transfer and aerodynamic performance in worn squealer tip gap of a high-pressure gas
turbine stage were numerically investigated. Effects of the starting location of wear and wear …