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RISDiscussion: “Transonic Cascade Flow Solved by Separate Supersonic and Subsonic Computations With Shock Fitting” (Wu, Wenquan, Wu, Chung-Hua, and Yu, Dabang, 1985, ASME J. Eng. Gas Turbines Power, 107, pp. 329–335)
Publisher: The American Society of Mechanical Engineers (ASME)
Discussion: “Off-Design Performance of Supersonic Compressors With Fixed and Variable Geometry” (Broichhausen, K.-D., Gallus, H. E., and Mönig, R., 1988, ASME J. Turbomach., 110, pp. 312–321)
Publisher: The American Society of Mechanical Engineers (ASME)
Off-Design Transition and Separation Behavior of a CDA Cascade
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The design of modern axial flow compressor blade sections as well as the code validation require experimental information about the transition and separation behavior of blade surface boundary ...
An Investigation of a Strong Shock-Wave Turbulent Boundary Layer Interaction in a Supersonic Compressor Cascade
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Experiments have been performed in a supersonic cascade facility to elucidate the fluid dynamic phenomena and loss mechanism of a strong shock-wave turbulent boundary layer interaction in a ...
Closure to “Discussion of ‘An Investigation of a Strong Shock-Wave Turbulent Boundary Layer Interaction in a Supersonic Compressor Cascade’” (1992, ASME J. Turbomach., 114, p. 503)
Publisher: The American Society of Mechanical Engineers (ASME)
Experimental Cascade Analysis of a Transonic Compressor Rotor Blade Section
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: A transonic compressor rotor blade cascade was tested in order to elucidate the flow behavior in the transonic regime and to determine the performance characteristic in the whole operating range ...
Some Experimental Results of Two-Dimensional Compressor Cascades at Supersonic Inlet Velocities
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The paper presents two-dimensional cascade results which have been obtained in transonic and supersonic cascade windtunnels. The upstream Mach number range is 1,0 ≤ M 1 ≤ 1,4. Tests have been ...
Inlet Flow Angle Determination of Transonic Compressor Cascades
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Tests of transonic compressor cascades require special measuring techniques to determine the inlet flow angle around sonic inlet flow conditions. One of the main requirements for these methods ...
Design and Testing of a Controlled Diffusion Airfoil Cascade for Industrial Axial Flow Compressor Application
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Similar to jet engine development, modern design methods are used today to improve the performance of industrial compressors. In order to verify the loading limits, a cascade profile representative ...
Experimental Investigation of the Performance of a Supersonic Compressor Cascade
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Results are presented from an experimental investigation of a linear, supersonic compressor cascade tested in the supersonic cascade wind tunnel facility at the DFVLR in Cologne, Federal Republic ...