Inlet guide vanes (IGV) of high temperature gas turbines require an effective trailing edge cooling. But this cooling influences significantly the aerodynamic performance caused by the unavoidable thickening of the trailing edge and the interference of the cooling flow with the main flow.
As part of a comprehensive research programme an inlet guide vane was designed and manufactured with two different trailing edge shapes. As a general result turns out from the cascade tests, that the flow behaviour upstream of the trailing edge remains unchanged. The homogeneous values downstream show higher turning and higher losses for the cut-back blade, especially in the supersonic range. Additional test were conducted with carbon dioxide ejection, in order to analyse the mixing process downstream of the cascade.