Inlet guide vanes (IGV) of high-temperature gas turbines require an effective trailing edge cooling. But this cooling significantly influences 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 program, an inlet guide vane was designed and manufactured with two different trailing edge shapes. The results from the cascade tests show that the flow behavior 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 tests were conducted with carbon dioxide ejection, in order to analyze the mixing process downstream of the cascade.

1.
Amecke, J., “Anwendung der transsonischen A¨hnlichkeitsregel auf die Stro¨mung durch ebene Schaufelgitter,” V DI-Forschungsheft, No. 540, 1970.
2.
Amecke, J., “Data Reduction of Wake Flow Measurements With Plane Cascades,” DLR-Report IB 222-90 A 06, 1990.
3.
Baines, N. C., Kiock, R., Lehthaus, F., and Sieverding, C. H., “A Comparison of Aerodynamic Measurements of the Transonic Flow Through a Plane Turbine Cascade in Four European Wind Tunnels,” presented at the 8th Symposium on Measuring Techniques for Transonic and Supersonic Flow in Cascades and Turbomachines, Genoa, Italy, 1985.
4.
Gieß, P.-A., “Berechnung der Abstro¨mwinkel und Verluste bei sub- und transsonisch durchstro¨mten Turbinengittern,” V DI-Forschungsheft, No. 657, 1999.
5.
Heinemann, H.-J., “The Test-Facility for Rectilinear Cascades (EGG) of the DFVLR,” DFVLR-Report IB 222-83 A 14, 1983.
6.
Ho¨hler, G., and Baumgarten, D., “Boundary Layer and Turbulence Measurements in Test-Rig-ETW,” DFVLR-Report IB 222-81 A 20, 1981.
7.
Ko¨llen, O., and Koschel, W., “Effect of Film Cooling on the Aerodynamic Performance of a Turbine Cascade,” AGARD-CP-390, Heat Transfer and Cooling in Gas Turbines, 65th PEP Symposium, Bergen, 1999.
8.
Kost, F. H., and Holmes, A. T., “Aerodynamic Effect of Coolant Ejection in the Rear Part of Transonic Rotor Blades,” AGARD-CP-390, Heat Transfer and Cooling in Gas Turbines, 65th PEP Symposium, Bergen, 1999.
9.
Oldfield, M. L. G., Schultz, D. L., and Nicholson, J. H., “Loss Measurements Using a Fast Traverse in an ILPT Transient Cascade,” presented at: 6th Meeting on Measuring Techniques in Transonic and Supersonic Flows in Cascades and Turbomachines, Lyon, Oct. 15-16, 1981.
10.
Sieverding
C. H.
, “
The Influence of Trailing Edge Ejection on the Base Pressure in Transonic Turbine Cascades
,”
ASME Journal of Engineering for Power
, Vol.
105
,
1983
, pp.
215
222
.
This content is only available via PDF.
You do not currently have access to this content.