IGTC-1 Experimental Investigation to Improve the Aerodynamic Performance of a Supercritical Airfoil in a Linear Cascade(Session A-1 CASCADE PERFORMANCE)

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概要

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• A new linear wind-tunnel and different measuring techniques were prepared for a detailed experimental investigation of an inverse compressor blade design in order to improve its aerodynamic performance. Different experimental investigation techniques gave a comprehensive insight into complex flow phenomena and their interaction. The influence of inlet Mach number and incidence angle on the boundary layer development could be described by a comparison of all results. Especially hot-film measurements and prediction with an integral boundary layer method proved to be excellent tools for this purpose. Additional losses were found caused by a vortex system within the separated boundary layer of the blade suction surface for the effect of increased blade loading. The experimental results were also used for the validation of numerical codes. Finally, the stator blade section was redesigned and an increased operating range and a lower loss level could be achieved.

• 公益社団法人日本ガスタービン学会の論文

著者

• Losch-schloms R.

  Institut Fur Strahlantriebe Und Turboarbeitsmaschinen Rwth Aachen

• Gallus H.E.

  Institut fur Strahlantriebe und Turboarbeitsmaschinen, RWTH Aachen

• Katoh Y.

  Power & Industrial Systems R & D Division, Hitachi Ltd.

• Kashiwabara Y.

  Department of Mechanical Systems Engineering, Kanagawa Institute of Technology

• Kashiwabara Y.

  Department Of Mechanical Systems Engineering Kanagawa Institute Of Technology

• Gallus H.e.

  Institut Fur Strahlantriebe And Turboarbeitsmaschinen Technische Hochschule Aachen

関連論文

• IGTC-1 Experimental Investigation to Improve the Aerodynamic Performance of a Supercritical Airfoil in a Linear Cascade(Session A-1 CASCADE PERFORMANCE)
• IGTC-68 MEASUREMENT OF 3-D UNSTEADY FLOW DOWNSTREAM OF ROTOR AND STATOR BLADES IN AXIAL-FLOW COMPRESSORS(Session B-8 Unsteady Aerodynamics I)
• TS-34 3D Navier-Stokes Simulation of a Transonic Flutter Cascade near Stall Conditions(Session B-3: Advanced Numerical Analysis of Cascade)
• TS-43 Unsteady Flow Phenomena in a Three Stage Axial Compressor with Controlled Diffusion Airfoils(Session B-6: Unsteady Flow 3)
• IGTC-S1 Recent Research Work on Turbomachinery Flow(Special Lecture I)

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