Numerical simulation of unsteady blade row interactions induced by passing wakes

Kulisa, Pascale; Dano, Cédric

doi:10.1016/j.euromechflu.2005.08.001

Cited by 7 publications

(2 citation statements)

References 15 publications

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“…However, the cylindrical type head extended the range with hole separation angle of 30 degrees. In addition to these studies, the numerical simulations have also been used to study the unsteady wake effects due to rotating struts [ 6 ] on turbine blades. The rotating probe [ 7 ] has different effects on the channel with a noticeable reduction in axial velocity and static pressure.…”

Section: Introductionmentioning

confidence: 99%

Numerical study of probe parameters on performance of a transonic axial compressor

Islam

2021

PLoS ONE

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The paper shows the effect of the probe on the performance of a transonic axial speed compressor. The unobstructed flow case with the experimental data was validated and used as a guide for all subsequent study cases. The aerodynamic performance for different probe parameters were calculated numerically using ANSYS-CFX. This covered the results on compressor output from changing probe axial positions, the radial immersion depths, the size of the probe, and the total number of probes. The findings were evaluated in relation to the total pressure ratio, performance, margin of deflation and stability. The velocity part distributions further showed that the probe block and raises the flow Mach value, which is the explanation why the compressor rotor’s total pressure ratio is lost. In fact, the parameters of the sample will significantly influence the calculation outcomes and affect the standard margin. The range of stability was also affected, which changes the performance trend from the choke to the stall. Consequently, the collection of correct probe parameters with fewer impact on compressor output is addressed.

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Section: Introductionmentioning

confidence: 99%

Numerical study of probe parameters on performance of a transonic axial compressor

Islam

2021

PLoS ONE

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“…In recent years, unsteady flow phenomena in both centrifugal and axial compressors have been, and continue to be, of considerable interest to design engineers and scientists. Most investigations are focused on axial turbomachinery [ 18 – 21 ], and investigations on centrifugal turbomachinery are less numerous; furthermore, investigations on the centrifugal compressor are mainly focused on the unsteady interactions between the impeller and the diffuser [ 12 – 16 ]. Most studies on the adjustable IGVs are with a view to changing the inlet boundary of the impeller, then to improve the overall aerodynamic performance of the stage [ 4 – 6 , 22 ].…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical analysis of the unsteady influence of an inlet guide vane

Fan

Wei

2011

Proceedings of the Institution of Mechanical Engineers, Part C:

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The unsteady inlet guide vane (IGV)–impeller–diffuser interaction in a centrifugal compressor is investigated numerically and experimentally under different IGV prewhirl angles. The influence of IGV prewhirl angle on the flowfield and the unsteadiness of the impeller and diffuser are studied, and the mechanism of the unsteady IGV–impeller–diffuser interaction is explored. Results show that quite fair quantitative agreements are achieved between the predicted and measured flowfield. The IGV wake can decrease the unsteadiness on the impeller and diffuser, and the reduction of the unsteadiness caused by the IGV is a function of the IGV prewhirl angle. The unsteadiness in the diffuser with negative IGV angles is larger than that for positive prewhirl angles. The low-frequency oscillations inside the flowfield are induced by the IGV. When IGV prewhirl occurs, the basic frequency of the unsteady flow in the vaneless diffuser is mainly half of the blade passing frequency of the impeller. In practice, the IGV prewhirl angle can be adjusted to avoid unsteady vibrations in some off-design conditions, with reliability and performance improved simultaneously.

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Effects of axial gap on aerodynamic force and response of shrouded and unshrouded blade

Jiang

Cai

et al. 2017

Sci. China Technol. Sci.

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Numerical simulation of unsteady blade row interactions induced by passing wakes

Cited by 7 publications

References 15 publications

Numerical study of probe parameters on performance of a transonic axial compressor

Numerical study of probe parameters on performance of a transonic axial compressor

Experimental and numerical analysis of the unsteady influence of an inlet guide vane

Effects of axial gap on aerodynamic force and response of shrouded and unshrouded blade

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