Effect of Rotor Tip Winglet on the Performance and Stability of a Transonic Axial Compressor

Shivaramaiah, Subbaramu; Nagpurwala, Quamber H.; Varpe, Mahesh K.; Narahari, H. K.

doi:10.1115/gtindia2017-4686

Cited by 5 publications

(3 citation statements)

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“…Niu et al 23 illustrated that the pressure side winglet can greatly expand the compressor stability margin. Varpe et al 24 revealed the influence of pressure and suction side winglet in a transonic rotor, and confirmed the most substantial improvement caused by the suction side winglet.…”

Section: Introductionmentioning

confidence: 88%

Effects of fusion height of tip winglet on the clearance flow in a compressor cascade

Sun

Zhong

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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The leakage flow generated by rotor clearance seriously affects efficiency and stability of a compressor. In order to reduce the effect of leakage flow, the tip winglet has been applied at the tip of a transonic compressor cascade. Numerical simulation has been used to investigate the influence of tip winglets with different fusion heights on the flow field structure. Furthermore, the effect of winglets was analyzed under different clearance heights and incidence angles. Results reveal that the winglet can weaken the kinetic energy of the leakage flow. The development of the leakage vortex along the pitchwise is suppressed, and the total pressure loss is decreased near the tip. The increase in the tip separation vortex scale leads to a remarkable decrease in the leakage flow rate. With the increase in fusion height, the scale of tip separation vortex decreases gradually, and the suppression effect on the leakage flow rate is weakened. The optimal scheme can reduce the loss by 3.3% and leakage flow rate by 13.4%. The suppression effect of the winglet on flow loss increases gradually with the increase in incidence angle. Moreover, the suppression effect of the winglet on leakage flow and flow loss increases first and then decreases with the increase in tip clearance.

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Section: Introductionmentioning

confidence: 88%

Effects of fusion height of tip winglet on the clearance flow in a compressor cascade

Sun

Zhong

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…By changing the structure of the casing or blades, they reallocate the flow rate and blade loading in the tip region and extend the operating range of compressors. Typical passive flow control methods include casing treatment [2][3][4], blade tip winglets [5,6], and vortex generators [7,8]. However, passive control methods will inevitably cause a significant penalty in the efficiency and the pressure ratio [9].…”

Section: Introductionmentioning

confidence: 99%

Characteristics of a Fluidic Oscillator with Low Frequency and Low Speed and Its Application to Stall Margin Improvement

et al. 2022

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Active flow control methods are commonly used in expanding the operating range of compressors. Indeed, unsteady active control methods are the main focus of researchers due to their effectiveness. For constructing an unsteady active control system, reliable actuators are significant. To compare with conventional actuators such as synthetic jet actuators and rotating valves, fluidic oscillators have structurally robust characteristics and can generate self-excited and self-sustained oscillating jets, which leads to its higher applicability in compressors under severe working conditions. Thus, to explore the feasibility of unsteady active control systems by the usage of fluidic oscillators, a low-frequency and low-speed oscillator is first designed and experimentally studied for improving the stability of a low-speed axial flow compressor. During the experiments, a special casing is designed to install 15 uniformly distributed oscillators in the tip region of compressor. Based on the unsteady micro injections of the rotor tip with rotor rotation frequency, the results indicate that the frequency/period of oscillators are flexible, in which the values are decoupled with the variation of inlet pressure. When the inlet-to-outlet pressure ratio of the oscillator is in the range of 1.1~2.0, the maximum velocity ranges from 30 m/s to 80 m/s. Moreover, the mass flow rate of the single oscillator only varies from 0.017‰ to 0.059‰ from the designed compressor mass flow rate. For the improvement of the compressor stall margin, the value is 3.45% when the total mass flow of oscillators is 0.08% of the designed compressor mass flow.

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“…Stockhaus et al [6] found that PSS helps to reduce tip leakage flow. It should be noted that tip squealer geometry is very different with blade winglet [17,18], although both are targeted to control tip clearance flow.…”

Section: Introductionmentioning

confidence: 99%

Parametric study of rotor tip squealer geometry on the aerodynamic performance of a high subsonic axial compressor stage

Yang

Wang

Zhang

et al. 2021

J Braz. Soc. Mech. Sci. Eng.

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Rotor with tip squealer is often used in axial compressor of aircraft engine; however, its effect on the aerodynamic performance of axial compressor is not well understood. The purpose of this paper is to numerically investigate the effect of squealer on the performance of a 1.5-stage axial compressor. In comparison with flat tip, suction and pressure side squealers (SSS and PSS) with different height and thickness are implemented on the rotor blade of the compressor stage. Numerical result shows that pressure ratio is increased slightly under different working conditions with SSS. At the reference working point (RWP), SSS helps to increase mass flow while PSS reduces both mass flow and efficiency. Detailed analysis indicates that blade tip loading rises due to SSS while PSS introduces more losses in the tip region. When squealer is used, the amount of tip leakage flow stays almost unchanged, while vortex trajectory and distribution of leakage flow within tip gap are different. PSS enhances tip leakage flow near the leading edge, which makes the mixing of tip leakage flow and main flow faster and stronger.

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Effect of Rotor Tip Winglet on the Performance and Stability of a Transonic Axial Compressor

Cited by 5 publications

References 0 publications

Effects of fusion height of tip winglet on the clearance flow in a compressor cascade

Effects of fusion height of tip winglet on the clearance flow in a compressor cascade

Characteristics of a Fluidic Oscillator with Low Frequency and Low Speed and Its Application to Stall Margin Improvement

Parametric study of rotor tip squealer geometry on the aerodynamic performance of a high subsonic axial compressor stage

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