Unsteady tip clearance flow in an isolated axial compressor rotor

Zhang, Hongwu; Deng, Xiaoyun; Chen, Jingyi; Huang, Weiguang

doi:10.1007/s11630-005-0004-4

Cited by 36 publications

(29 citation statements)

References 18 publications

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“…Several peaks of considerable magnitudes can be observed at each chordwise position, indicating the occurrence of the spike stall. This conclusion is in a good agreement with the results of Zhang et al 13 and Vo et al, 15 which have shown that the periodic characteristics of the tip leakage flow can be recognized by existence of some peaks in the frequency spectrum at the near-stall condition. Zhang et al 13 have shown that the self-induced unsteadiness is caused by the interaction of the main inflow with the tip leakage flow and fluctuates with a frequency lower than the blade passing frequency.…”

Section: Frequency Analysissupporting

confidence: 92%

“…Hence, in addition to performing various kinds of casing treatments in enhancing the compressor stall margin, some researchers like Rae and Breuer, 11 Mailach et al 12 and Zhang et al 13 focused on studying the characteristics of this complex flow in details. Some investigations have been carried out to study the relation between the unsteady tip leakage flow and the spike stall inception as precursor of the fully developed rotating stall.…”

Section: Introductionmentioning

confidence: 99%

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Alleviation of spike stall in axial compressors utilizing grooved casing treatment

Taghavi-Zenouz

Abbasi

2015

Chinese Journal of Aeronautics

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This article deals with application of grooved type casing treatment for suppression of spike stall in an isolated axial compressor rotor blade row. The continuous grooved casing treatment covering the whole compressor circumference is of 1.8 mm in depth and located between 90% and 108% chord of the blade tip as measured from leading edge. The method of investigation is based on time-accurate three-dimensional full annulus numerical simulations for cases with and without casing treatment. Discretization of the Navier-Stokes equations has been carried out based on an upwind second-order scheme and k-x-SST (Shear Stress Transport) turbulence modeling has been used for estimation of eddy viscosity. Time-dependent flow structure results for the smooth casing reveal that there are two criteria for spike stall inception known as leading edge spillage and trailing edge backflow, which occur at specific mass flow rates in near-stall conditions. In this case, two dominant stall cells of different sizes could be observed. The larger one is caused by the spike stall covering roughly two blade passages in the circumferential direction and about 25% span in the radial direction. Spike stall disturbances are accompanied by lower frequencies and higher amplitudes of the pressure signals. Casing treatment causes flow blockages to reduce due to alleviation of backflow regions, which in turn reduces the total pressure loss and increases the axial velocity in the blade tip gap region, as well as tip leakage flow fluctuation at higher frequencies and lower amplitudes. Eventually, it can be concluded that the casing treatment of the stepped tip gap type could increase the stall margin of the compressor. This fact is basically due to retarding the movement of the interface region between incoming and tip leakage flows towards the rotor leading edge plane and suppressing the reversed flow around the blade trailing edge.

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Section: Frequency Analysissupporting

confidence: 92%

Section: Introductionmentioning

confidence: 99%

Alleviation of spike stall in axial compressors utilizing grooved casing treatment

Taghavi-Zenouz

Abbasi

2015

Chinese Journal of Aeronautics

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“…With tip clearance of 2.2% tip chord the region of influence by the tip leakage flow not only reaches the pressure side of the neighboring blade, but also penetrates further down along the span of the blade. According to reference [6,10], self-induced unsteadiness of tip leakage flow appears when tip leakage flow is strong enough to change the original pressure distribution on adjacent blade pressure surface. It is therefore not surprised that only the case with 2.2% tip chord exhibits the unsteadiness at this mass flow rate, while the other two cases are steady.…”

Section: Resultsmentioning

confidence: 99%

“…Zhang et al [6] demonstrated tip leakage vortex became unsteady at high loading operating conditions with relatively large tip clearance in a low-speed compressor rotor. When studying a high-speed compressor rotor, Yamada et al [7] found that breakdown of tip leakage vortex occurring in the compressor rotor resulted in self-sustained flow oscillation in the tip leakage flow field at near-stall operating condition as well as at near peak efficiency condition.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation on the effect of tip clearance size on unsteadiness in tip clearance flow

Feng

Zhang

et al. 2008

J. Therm. Sci.

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Unsteadiness of tip clearance flow with three different tip clearance sizes is numerically investigated in this paper.NASA Rotor 67 is chosen as the computational model. It is found that among all the simulated cases, the unsteadiness exists when the size of the tip clearance is equal to or larger than design tip clearance size. The relative total pressure coefficient contours indicate that region of influence by tip leakage flow augments with the increase of tip clearance size at a fixed mass flow rate. Root Mean Square contours of static pressure distribution in the rotor tip region are provided to illustrate that for design tip clearance (1.1% tip chord) the strongest fluctuating region is located on pressure side of blade near leading edge, while for the larger tip clearance (2.2% tip chord), it is in the region of the interaction between the shock wave and the tip leakage flow.

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“…So far, there are three different views about the occurrence of unsteadiness of tip clearance flow. Mailach et al [3] has shown that the investigated low speed compressor develops a two passage periodic tip leakage vortex pattern, which is called 'rotating instabilities' .Zhang et al [4] and Tong et al [5] found that prior to the initiation of spike inception, the tip leakage flow shows obvious self-induced unsteadiness caused by the fluctuation of the pressure difference across the tip clearance in their computational and experimental work, respectively. Such unsteadiness has been proved to have some relations with the initiation of a spike inception by Lin et al [6].…”

Section: Introductionmentioning

confidence: 99%

A study of the unsteady tip flow field of a transonic compressor

Zhang

et al. 2011

J. Therm. Sci.

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An experimental investigation on the unsteady tip flow field of a transonic compressor rotor has been performed.The casing-mounted high frequency response pressure transducers were arranged along both the blade chord and the blade pitch. The chord-wise ones were used to indicate both the ensemble averaged and time varying flow structure of the tip region of the rotor at different operating points under 95% design speed and 60% design speed.The pitch-wise circumferential transducers were mainly used to analyze the unsteadiness frequency of the tip leakage flow in the rotor frame at the near stall condition. The contours of casing wall pressure show that there were two clear low pressure regions in blade passages, one along the chord direction, caused by the leakage flow and the other along the tangential direction, maybe caused by the forward swept leading edge. Both low pressure regions were originated from the leading edge and formed a scissor-like flow pattern. At 95% design speed condition, the shock wave interacted with the low pressure region and made the flow field unsteady. With the mass flow reduced, the two low pressure regions gradually contracted to the leading edge and then a spike disturbance emerged.

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Unsteady tip clearance flow in an isolated axial compressor rotor

Cited by 36 publications

References 18 publications

Alleviation of spike stall in axial compressors utilizing grooved casing treatment

Alleviation of spike stall in axial compressors utilizing grooved casing treatment

Numerical simulation on the effect of tip clearance size on unsteadiness in tip clearance flow

A study of the unsteady tip flow field of a transonic compressor

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