Aerodynamic Interference Between Moving Blade Rows

Kemp, Nelson H.; Sears, W. R.

doi:10.2514/8.2758

Cited by 102 publications

(19 citation statements)

References 4 publications

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“…Interactions was published In 1953 by Kemp and Sears [50,51] who studied the aerodynamic Interference between rotor and stater blade rows for Lefcort considered that the unsteady forces In turbomachlnes were due to four main effects: a circulation effect, a blade thickness effect, a wake effect, and a wake distortion effect. The above mentioned blade-row…”

Section: B Modeling Effortsmentioning

confidence: 99%

“…A comparison of their numerical results with experiment indicated that there was still much to be learned about the nature of blade-row interactions before a numerical solution scheme for a complete stage would be capable of predicting the actual flows. In 1982, Krammer [50] developed a time marching scheme for computing the unsteady blade forces in turbomachines, which he based on potential flow theory and simulated viscous wakes. Blade surfaces were modeled by vortex distributions and viscous wakes were simulated by contra-rotating vortex rows.…”

Section: B Modeling Effortsmentioning

confidence: 99%

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Unsteady flows in a single-stage transonic axial-flow fan stator row

Hathaway

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Section: B Modeling Effortsmentioning

confidence: 99%

Section: B Modeling Effortsmentioning

confidence: 99%

Unsteady flows in a single-stage transonic axial-flow fan stator row

Hathaway

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“…It is generated by the interaction of the pressure fields surrounding the adjacent blade rows, Fig.6. It can be shown (8) and (12) that the unsteady circulation generated on a stator by the rotor steady circulationr or is given by 00 6s, 6 r are, respectively, the solidities of the stator and the rotor. The other parameters are defined in Fig.6.…”

Section: Potential Interaction Noisementioning

confidence: 99%

Fan Compressor Noise Reduction

Benzakein

Kazin

1969

ASME 1969 Gas Turbine Conference and Products Show

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A study of various fan/compressor noise reduction methods is presented. The analytical treatment of the basic mechanisms of fan/compressor noise generation is described. The results are presented in parametric form and indicate the effects of fan/compressor design, number of blades, vane/blade ratio, aerodynamic parameters, and blade row spacing on pure tone noise reduction. These results are based on nonsteady aerodynamic treatment of wake and potential interaction effects and theoretical extensions of spinning mode theories.

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“…1950s by Kemp and Sears[8] [9].Kemp and Sears applied a linearized potential flow solution to the vane-blade interaction problem. They concluded that the unsteady pressures could be as high as 18 percent of the steady-state pressure.…”

mentioning

confidence: 99%

Unsteady Aerodynamic Interaction in a Closely Coupled Turbine Consistent With Contrarotation

Ooten

Anthony

Lethander

et al. 2016

Journal of Turbomachinery

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The focus of the study presented here was to investigate the interaction between the blade and downstream vane of a stage-and-one-half transonic turbine via computation fluid dynamic (CFD) analysis and experimental data. A Reynolds-averaged Navier–Stokes (RANS) flow solver with the two-equation Wilcox 1998 k–ω turbulence model was used as the numerical analysis tool for comparison with all of the experiments conducted. The rigor and fidelity of both the experimental tests and numerical analysis methods were built through two- and three-dimensional steady-state comparisons, leading to three-dimensional time-accurate comparisons. This was accomplished by first testing the midspan and quarter-tip two-dimensional geometries of the blade in a linear transonic cascade. The effects of varying the incidence angle and pressure ratio on the pressure distribution were captured both numerically and experimentally. This was used during the stage-and-one-half post-test analysis to confirm that the target corrected speed and pressure ratio were achieved. Then, in a full annulus facility, the first vane itself was tested in order to characterize the flowfield exiting the vane that would be provided to the blade row during the rotating experiments. Finally, the full stage-and-one-half transonic turbine was tested in the full annulus cascade with a data resolution not seen in any studies to date. A rigorous convergence study was conducted in order to sufficiently model the flow physics of the transonic turbine. The surface pressure traces and the discrete Fourier transforms (DFT) thereof were compared to the numerical analysis. Shock trajectories were tracked through the use of two-point space–time correlation coefficients. Very good agreement was seen when comparing the numerical analysis to the experimental data. The unsteady interaction between the blade and downstream vane was well captured in the numerical analysis.

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Aerodynamic Interference Between Moving Blade Rows

Cited by 102 publications

References 4 publications

Unsteady flows in a single-stage transonic axial-flow fan stator row

Unsteady flows in a single-stage transonic axial-flow fan stator row

Fan Compressor Noise Reduction

Unsteady Aerodynamic Interaction in a Closely Coupled Turbine Consistent With Contrarotation

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