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Study of the Effect of a Blade Tip Notch Damage on the Aerodynamic Performance of Transonic Compressor Rotors

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Abstract

To investigate the effect of various notch damages at the blade tip of a pressurized rotor blade on the aerodynamic performance, the repair margin of blade tip notch damage and obtaining its spacing in the wing polish in size is explored. Based on the Rotor 37, a model of a blade with a notch depth between 0–0.3 mm and 0.3–5 mm is obtained, and the calculation model of the single-pass aerodynamic performance before and after the damage is constructed. Numerical simulations of the full 3D viscous flow field are carried out for the design and near-surge conditions, and the data are compared and analysed. The following results are obtained: the mass flow rate increases with the notch depth; the pressure boosting capacity slightly increases and then significantly decreases when the notch depth exceeds 1 mm; the stability margin is lower than 15% after the tip notch damage exceeds 0.23 mm and decreases with the notch depth; and the tip notch does not significantly affect the aerodynamic performance of the intact blade section at the height under the notch. When the notch depth exceeds 0.23 mm, the blade starts to show a near-stall trend, and when the notch depth approaches 5 mm, it demonstrates the near-stall operating condition.

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Funding

The work was carried out with financial support from the National Natural Science Foundation of China (NNSFC) (Grant no. U1933202).

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  1. Civil Aviation University of China, Tianjin, China

    J. Tang, Z. H. Zhong, X. Lu & L. W. Wang

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  1. J. Tang
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  2. Z. H. Zhong
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  4. L. W. Wang
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Correspondence to Z. H. Zhong.

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Tang, J., Zhong, Z.H., Lu, X. et al. Study of the Effect of a Blade Tip Notch Damage on the Aerodynamic Performance of Transonic Compressor Rotors. Fluid Dyn 58, 1623–1639 (2023). https://doi.org/10.1134/S0015462823600803

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  • DOI: https://doi.org/10.1134/S0015462823600803

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