Laser anemometry study of the flow field in a transonic compressor rotor

Weyer, H.; Dunker, R. J.

doi:10.2514/6.1978-1

Cited by 5 publications

(3 citation statements)

References 2 publications

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“…Detailed laser-two-focus velocimetry measurements of the flow in an axial single stage transonic compressor rotor were conducted at DFVLR (Weyer and Dunker, 1978;Dunker et al, 1977). These data serve as a widely used test case for 3D calculation methods.…”

Section: Dfvlr Compressor Rotormentioning

confidence: 99%

Use of Advanced CFD Codes in the Turbomachinery Design Process

Novák

Schäfer

Schönung

et al. 1992

Volume 1: Turbomachinery

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This paper describes the development and application of CFD codes, based on time-marching finite-volume formulations to the flow analysis in blade cascades, blade rows and stages of modern turbomachines. Special attention is paid to the reduction of the numerical dissipation of finite-volume discretization schemes, the numerical simulation of shock waves and to viscous effects. Furthermore, the application of solution-adaptive structured and unstructured computational grids is investigated. Finally, the ability of time-marching finite-volume methods to simulate three-dimensional flow effects in turbomachinery bladings is demonstrated.

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Section: Dfvlr Compressor Rotormentioning

confidence: 99%

Use of Advanced CFD Codes in the Turbomachinery Design Process

Novák

Schäfer

Schönung

et al. 1992

Volume 1: Turbomachinery

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“…Whereas the three-dimensional nature of transonic compressor flow field has been previously studied in many works (1)(2)(3)(4)(5)(6)(7), fewer are the investigations concerning the intra-blade flow field of fully supersonic compressor rotors.…”

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confidence: 99%

Laser Two-Focus Anemometry Investigation of the Flow Field Within a Supersonic Axial Compressor Rotor

Trébinjac

Vouillarmet

1990

Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation;

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Laser anemometer measurements have been performed within and downstream of a supersonic single-stage high-pressure compressor. At design point and with standard upstream conditions the maximum relative Mach number varies from 1.3 at the tip to 1.1 at the hub. The stage total pressure ratio is 1.84 and the specific mass flow 180 kg/s/m2. The laser two-focus anemometer has been completely designed in the Laboratory; its originality being the use of a counting technique instead of the classical multichannel analyzer one. The data acquisition and reduction procedures are presented here. A comprehensive evaluation of the global flow-field is in the scope of this paper. For that, the intra-blade flow field is described and the shock pattern is discussed. Furthermore, the experimental results are compared with both inviscid and viscous three-dimensional numerical simulations. The viscous computation is based on the Navier-Stokes solution using a mixing length turbulence model. The good agreement observed in this last case shows off the necessity of taking into account the viscous effects in a supersonic compressor flow calculation.

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“…A considerable contribution for the new developments and designs was the progress made in optical measurement techniques and computational methods, leading to a deeper understanding of the loss mechanisms of supersonic relative flow in compressors (e.g. Calvert & Stapleton, 1994;Hah & Reid, 1992;Ning & Xu, 2001;Strazisar, 1985;Weyer & Dunker, 1978). Fig.…”

Section: Introductionmentioning

confidence: 99%