This paper reports the external convective heat transfer distribution of a modern single-stage transonic turbine together with the physical interpretation of the different shock interaction mechanisms. The measurements have been performed in the compression tube test rig of the von Karman Institute using single- and double-layered thin film gauges. The three pressure ratios tested are representative of those encountered in actual aeroengines, with ranging from 1.07 to 1.25 and a Reynolds number of about . Three different rotor blade heights (15%, 50%, and 85%) and the stator blade at midspan have been investigated. The measurements highlight the destabilizing effect of the vane left-running shock on the rotor boundary layer. The stator unsteady heat transfer is dominated by the fluctuating right-running vane trailing edge shock at the blade passing frequency.
Issue Section:
Research Papers
Keywords:
aerospace engines,
blades,
boundary layers,
convection,
flow instability,
gas turbines,
rotors,
shock waves,
stators,
transonic flow
Topics:
Blades,
Gages,
Heat transfer,
Pressure,
Rotors,
Shock (Mechanics),
Stators,
Turbines,
Boundary layers
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