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Research on turbine blade squealer tip film holes arrangement and moving shroud

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Abstract

In this paper, the performance of the turbine blade squealer tip with film cooling has been studied detailed to highlight the impact of the relative motion between the blade tip and the shroud. A high-pressure turbine has been employed to perform the numerical simulation. Boundary conditions are consistent with the operating conditions of the plane cascade experiment in a transonic wind tunnel. The validation of the turbulent model and mesh independence test has been conducted based on the experimental results. The distribution of blade tip heat transfer coefficient (HTC) and film cooling effectiveness has been used to evaluate the blade tip performance. Two different relative speeds and three different film holes arrangements have been adopted and studied to understand its influence. Results show that with relative motion and film cooling, the blade tip overall aerothermal characteristics remains unchanged. But the local HTC on several regions has significantly changed due to the complex interaction among the leakage flow, coolant, and relative motion. And the relative motion has a significant impact on the coolant, which redirects the coolant towards the pressure side of the blade and changes the coolant coverage inside the cavity.

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Data availability

The data that support the findings of this study are available from the corresponding author upon reasonable request.

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Acknowledgements

This work is partially supported by the Aeronautical Science Foundation of China (2015ZB57003).

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Authors and Affiliations

  1. School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai, 200240, China

    Hao Luo, Xiaoqing Qiang & Bo Zhang

Authors
  1. Hao Luo
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  2. Xiaoqing Qiang
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  3. Bo Zhang
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Contributions

XQ contributed to the conception of the study and performed the experiment. BZ performed the experiment and contributed to the initialization of numerical simulation. HL conducted the numerical study, performed the data analyses, and wrote the manuscript.

Corresponding author

Correspondence to Xiaoqing Qiang.

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The authors declare that they have no conflict of interest.

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This article does not contain any studies with human or animal subjects performed by any of the authors.

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Luo, H., Qiang, X. & Zhang, B. Research on turbine blade squealer tip film holes arrangement and moving shroud. AS 5, 491–501 (2022). https://doi.org/10.1007/s42401-022-00139-9

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  • DOI: https://doi.org/10.1007/s42401-022-00139-9

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