Investigation of Performance and Rotor Tip Flow Field in a Low Speed Research Compressor with Circumferential Groove Casing Treatment at Varying Tip Clearance

Rolfes, Matthias; Lange, Martin; Mailach, Ronald

doi:10.1155/2017/4631751

Cited by 5 publications

(3 citation statements)

References 31 publications

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“…As the tip gap extends, a hump in the FFT spectra of the throttled operating points becomes prominent, while at the design point (Φ = 0.57), no change is detectable. The frequency of the hump is about 1/2 BPF for s/C = 2.6% and reduces to around 1/3 BPF for s/C = 4.3%, which corresponds to the previous observation in the other tests based on the LSRC [2,7]. Such unsteady disturbances indicated by the narrow-band region below the BPF are believed to be the RIs.…”

Section: Overall Performancesupporting

confidence: 86%

“…The RIs were found in those configurations with relatively large tip clearance. Rolfes et al [7] observed RI in a single stage build of the Dresden LSRC when the rotor tip clearance was increased to 2.5% chord length, and the mean frequency of the hump decreased with the tip gap extended. The amplitudes of RIs were damped by a circumferential groove casing treatment.…”

Section: Introductionmentioning

confidence: 99%

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Rotating Instabilities in a Low-Speed Single Compressor Rotor Row with Varying Blade Tip Clearance

et al. 2021

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When a compressor is throttled to the near stall point, rotating instability (RI) is often observed as significant increases of amplitude within a narrow frequency band which can be regarded as a pre-stall disturbance. In the current study, a single compressor rotor row with varying blade tip clearance (1.3%, 2.6% and 4.3% chord length) was numerically simulated using the zonal large eddy simulation model. The mesh with six blade passages was selected to capture the proper dynamic feature after being validated in comparison to the measured data, and the dynamic mode decomposition (DMD) approach was applied to the numerical temporal snapshots. In the experimental results, RIs are detected in the configurations with middle and large tip gaps (2.6% and 4.3% chord length), and the corresponding characterized frequencies are about 1/2 and 1/3 of the blade passing frequency, respectively. Simulations provide remarkable performance in capturing the measured flow features, and the DMD modes corresponding to the featured RI frequencies are successfully extracted and then visualized. The analysis of DMD results indicates that RI is essentially a presentation of the pressure wave propagating over the blade tip region. The tip leakage vortex stretches to the front part of the adjacent blade and consequently triggers the flow perturbations (waves). The wave influences the pressure distribution, which, in turn, determines the tip leakage flow and finally forms a loop.

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Section: Overall Performancesupporting

confidence: 86%

Section: Introductionmentioning

confidence: 99%

Rotating Instabilities in a Low-Speed Single Compressor Rotor Row with Varying Blade Tip Clearance

et al. 2021

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“…The change in tip clearance affects not only the rotor performance but also the downstream stator performance and the stability of the stage [15][16][17][18]. Howard and Puterbaugh [19] combined computational fluid dynamics(CFD) unsteady simulation calculations and experiments to study the effect of the tip clearance variation on the efficiency of the transonic small aspect ratio (average rotor aspect ratio = 0:57) axial compressor stage.…”

Section: Introductionmentioning

confidence: 99%

Effects of the Shock Wave Structure on the Tip Clearance Leakage Flow in Transonic Compressor Rotors

Zhou

2023

International Journal of Aerospace Engineering

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The interaction between shock waves and the tip clearance flow in a transonic compressor rotor has important effects on the tip clearance flow and the rotor aerodynamic performance. In this paper, two transonic rotors with a high pressure ratio are selected to study the tip flow, one of which has one normal shock wave at the blade tip and the other has two shock waves (an oblique shock wave and a normal shock wave) at the tip. The two rotors have the same meridional flow channel, design point flow rate, pressure ratio, and rotation speed to focus on the influence caused by the effect of the shock wave structure. The numerical results for the flow fields show the following conclusions. The strength of the two shock waves at the blade tip is weaker than that of one normal shock, and the former two shock waves are less stable than the latter. Therefore, with increasing tip clearance, the efficiency, pressure ratio, and stall margin of the rotor with the two shock waves decrease more rapidly. The static pressure difference between the pressure and suction sides of the tip clearance is the only driving factor of the tip clearance leakage flow, and the leakage flow depends on the local pressure difference and the secondary leakage caused by adjacent blades. The movement speed of the annular wall is less than that of the leakage flow, which has a minor blocking effect on the tip clearance leakage flow. The change in tip clearance has little effect on the chordal distribution of the static pressure difference and leakage flow rate per unit area, so the total leakage flow varies linearly with the tip clearance size.

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Influence of Tip Clearance on Flow Behavior and Noise Generation

Garcia

2018

Springer Theses

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Investigation of Performance and Rotor Tip Flow Field in a Low Speed Research Compressor with Circumferential Groove Casing Treatment at Varying Tip Clearance

Cited by 5 publications

References 31 publications

Rotating Instabilities in a Low-Speed Single Compressor Rotor Row with Varying Blade Tip Clearance

Rotating Instabilities in a Low-Speed Single Compressor Rotor Row with Varying Blade Tip Clearance

Effects of the Shock Wave Structure on the Tip Clearance Leakage Flow in Transonic Compressor Rotors

Influence of Tip Clearance on Flow Behavior and Noise Generation

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