Numerical investigation of tip clearance effects on rotating instability of a low-speed compressor

Li, Tao; Wu, Yadong; Ouyang, Huajiang

doi:10.1016/j.ast.2021.106540

Cited by 15 publications

(1 citation statement)

References 24 publications

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“…März [16] found through experiments and numerical simulations that RI only exists in the blade tip area during the stable operation of the compressor and it is especially obvious in the presence of a large stagger angle and a large tip clearance. Li et al [24] carried out a full annulus unsteady simulation for a low-speed axial compressor with and without clearance and found that when there was clearance, the transverse vortex in each passage and the shedding vortex at the rear of the blade suction side every two passages were related to RI.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Rotating Instability in an Axial Compressor with a Steady Swirl Distortion Inlet

Wang

et al. 2021

Energies

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In this paper, an experimental study was carried out on the rotating instability in an axial compressor subjected to inlet steady paired swirl distortion. In order to deepen the understanding of the rotating stall mechanism under inlet steady paired swirl distortion, the dynamic-wall static pressure near the rotor tip was monitored to characterize the flow in the rotor tip region at different circumferential stations. In the experiment, the dynamic characteristics of the rotor tip flow field at a stable operating point and during the process from the stable point to complete stall were measured. The results indicated that for the compressor with a 2 mm rotor tip clearance, the inlet paired swirl distortion induced rotating instability (RI) near the stall point, causing the compressor to enter stall in advance. Compared with the RI intensity of the clean inlet, the distortion with a swirling blade stagger angle (αst) of ±20° increased the RI intensity up to 69.8%, while for αst equal to ±40°, the RI intensity increased at most by 135.8%. As the rotor tip clearance increased to 3 mm, the co-rotating swirl in the paired swirl distortion inhibited the appearance of RI, while the counter-rotating part aggravated the development of RI. At the beginning, the process of the compressor rotating stall involved the alternation of short-scale disturbance and long-scale disturbance. The co-rotating swirl weakened the perturbation propagated from the counter-rotating swirl sector. Once the inhibition was no longer present, the short-scale disturbance rapidly developed into a long-scale disturbance and then entered the rotating stall.

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Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Rotating Instability in an Axial Compressor with a Steady Swirl Distortion Inlet

Wang

et al. 2021

Energies

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Modal Analysis of Axial Compressor Tip Rotating Instability under Varying Operating Conditions

Tian

et al. 2023

J. Therm. Sci.

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Investigation of tip leakage flow in spatial and temporal scales of axial isolated compressor rotor near stall

Wang

et al. 2023

J Braz. Soc. Mech. Sci. Eng.

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Numerical investigation of tip clearance effects on rotating instability of a low-speed compressor

Cited by 15 publications

References 24 publications

Experimental Investigation of Rotating Instability in an Axial Compressor with a Steady Swirl Distortion Inlet

Experimental Investigation of Rotating Instability in an Axial Compressor with a Steady Swirl Distortion Inlet

Modal Analysis of Axial Compressor Tip Rotating Instability under Varying Operating Conditions

Investigation of tip leakage flow in spatial and temporal scales of axial isolated compressor rotor near stall

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