Effect of differential tip clearance on the performance and noise of an axial compressor

Zhang, Ming; Dong, Xu; Li, Jia; Sun, Dakun; Sun, Xiaofeng

doi:10.1016/j.ast.2022.108070

Cited by 11 publications

(4 citation statements)

References 30 publications

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“…Tip clearance flow and its mixing with main flow and spanwise transport flow, including the interaction with shock waves in supersonic or transonic rotors, form a complex three-dimensional flow [1]. Studies show that the flow loss in the tip region accounts for approximately one-third of the total loss of the compressor, so the rotor tip region is a high loss region, usually also the stall initiation region [2][3][4][5][6][7]. The tip region of the rotor is the only region with high flow loss regardless of whether the pressure ratio is high or low [8,9].…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Introductionmentioning

confidence: 99%

“…The higher the rotor pressure ratio and the larger the tip clearance, the higher the flow loss in this region. In addition, tip leakage flow is also an important self-noise source [7,10,11].…”

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 results showed that the use of the foam metal casing treatment could reduce aerodynamic noise within a range of 0.18 dB∼1.6 dB. Zhang et al [19] used the experiment method to investigate the effect of differential tip clearances on the noise emissions of an axial compressor. The results showed that when the tip clearance was small, the sound pressure level (SPL) of the compressor was lowest.…”

Section: Introductionmentioning

confidence: 99%

An Explainable Prediction Model for Aerodynamic Noise of an Engine Turbocharger Compressor Using an Ensemble Learning and Shapley Additive Explanations Approach

Huang,

Ni,

Qiao

et al. 2023

Sustainability

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In the fields of environment and transportation, the aerodynamic noise emissions emitted from heavy-duty diesel engine turbocharger compressors are of great harm to the environment and human health, which needs to be addressed urgently. However, for the study of compressor aerodynamic noise, particularly at the full operating range, experimental or numerical simulation methods are costly or long-period, which do not match engineering requirements. To fill this gap, a method based on ensemble learning is proposed to predict aerodynamic noise. In this study, 10,773 datasets were collected to establish and normalize an aerodynamic noise dataset. Four ensemble learning algorithms (random forest, extreme gradient boosting, categorical boosting (CatBoost) and light gradient boosting machine) were applied to establish the mapping functions between the total sound pressure level (SPL) of the aerodynamic noise and the speed, mass flow rate, pressure ratio and frequency of the compressor. The results showed that, among the four models, the CatBoost model had the best prediction performance with a correlation coefficient and root mean square error of 0.984798 and 0.000628, respectively. In addition, the error between the predicted total SPL and the observed value was the smallest, at only 0.37%. Therefore, the method based on the CatBoost algorithm to predict aerodynamic noise is proposed. For different operating points of the compressor, the CatBoost model had high prediction accuracy. The noise contour cloud in the predicted MAP from the CatBoost model was better at characterizing the variation in the total SPL. The maximum and minimum total SPLs were 122.53 dB and 115.42 dB, respectively. To further interpret the model, an analysis conducted by applying the Shapley Additive Explanation algorithm showed that frequency significantly affected the SPL, while the speed, mass flow rate and pressure ratio had little effect on the SPL. Therefore, the proposed method based on the CatBoost algorithm could well predict aerodynamic noise emissions from a turbocharger compressor.

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“…Figurella et al [14] showed that the discrete noise could be observed in the BPF of a compressor and its harmonic frequencies. Zhang et al [15] explored the influence of differential tip clearance on the performance and noise of an axial compressor adopting the experiment method. The results indicated that the compressor's sound pressure level (SPL) was lowest at a relatively small tip clearance rather than zero.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Mechanism Study of Aerodynamic Noise Emission Characteristics from a Turbocharger Compressor of Heavy-Duty Diesel Engine Based on Full Operating Range

Huang

Wang

et al. 2023

Sustainability

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Heavy-duty diesel engines equipped with turbochargers is an effective way to alleviate energy shortage and reduce gas emissions, but their compressor aerodynamic noise emissions have become an important issue that needs to be addressed urgently. Therefore, to study the aerodynamic noise emission characteristics of a compressor during the full operating range, experimental and numerical simulation methods were used to analyze the aerodynamic noise emissions. The results showed that aerodynamic noise’s total sound pressure level (SPL) increased with increased speed under the test conditions. At low speeds, the total SPL of aerodynamic noise was affected by the mass flow of the compressor more obviously. The maximum difference of aerodynamic noise total SPL was 1.55 dB at 60,000 r/min under different mass flows. At the same speed, the compressor could achieve lower aerodynamic noise emissions by operating in the high-efficiency region (middle mass flows). In the compressor aerodynamic noises, the blade passing frequency (BPF) noise played a dominant role. The transient acoustic-vibration spectral characteristics and fluctuation pressure analysis indicated that BPF and its harmonic frequency noises were mainly caused by the unsteady fluctuation pressure. As the speed increased, the BPF noise contributed more to the total SPL of the aerodynamic noise, and its percentage was up to 75.35%. The novelty of this study was the analysis of the relationship between compressor aerodynamic noise and internal flow characteristics at full operating conditions. It provided a theoretical basis for reducing the heavy-duty diesel engine turbocharger compressor aerodynamic noise emissions.

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Effect of differential tip clearance on the performance and noise of an axial compressor

Cited by 11 publications

References 30 publications

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

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

An Explainable Prediction Model for Aerodynamic Noise of an Engine Turbocharger Compressor Using an Ensemble Learning and Shapley Additive Explanations Approach

Experimental and Mechanism Study of Aerodynamic Noise Emission Characteristics from a Turbocharger Compressor of Heavy-Duty Diesel Engine Based on Full Operating Range

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