An Evaluation of the Performance of a Novel Film Cooling Holes applied to Gas Turbine Blades

Authors

  • Amina Boudlal Department of Mechanical Engineering, University Djillali Liabes, Sidi Bel Abbes, Algeria
  • Faiza Ghezali Structural and Solid Mechanics Laboratory (LMSS), Department of Mechanical Engineering, University Djillali Liabes, Sidi Bel Abbes, Algeria
  • Abdelkader Lahcene Department of Mechanical Engineering, University Djillali Liabes, Sidi Bel Abbes, Algeria
Volume: 15 | Issue: 3 | Pages: 22306-22311 | June 2025 | https://doi.org/10.48084/etasr.10472

Received: 6 February 2025 | Revised: 28 February 2025 | Accepted: 7 March 2025 | Online: 26 March 2025


Corresponding author: Faiza Ghezali

Abstract

Modern gas turbine engines require a sophisticated cooling system design to achieve higher power output and efficiency. The present work aims to improve the film cooling effectiveness using a novel configuration based on an enlarged spanwise cooling hole. First, the numerical results are compared with experimental data of Fan-Shaped Holes (FSHs), which are widely used as a design in turbine blades. The proposed shape is designed to enhance the efficiency of the coolant jet across all cooling areas. The main operating parameters applied were a density ratio of 1.7 and a blowing ratio ranging from 0.5 to 2.5. The simulations were performed using three-dimensional Reynolds-averaged Navier–Stokes (RANS) analysis with the SST k-ω turbulence model. The comparison showed that the proposed design numerical results closely match the experimental data for FSHs. At lower blowing ratios (0.5), the proposed Diffused Shaped Hole (DSH) achieves higher area-averaged film cooling effectiveness than the FSH while maintaining the same coolant usage. At higher blowing ratios, the DSH provides a more uniform distribution and an improved cooling effectiveness on the film than the FSH.

Keywords:

blowing ratio, cooling effectiveness, fan-shaped hole, novel diffussed shaped hole, SST k-ω model

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How to Cite

[1]
Boudlal, A., Ghezali, F. and Lahcene, A. 2025. An Evaluation of the Performance of a Novel Film Cooling Holes applied to Gas Turbine Blades. Engineering, Technology & Applied Science Research. 15, 3 (Jun. 2025), 22306–22311. DOI:https://doi.org/10.48084/etasr.10472.

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