Study of Shaped Holes in Film Cooling for Spinning Turbine Blades

Articles in Press

Document Type : Full Length Research Article

Authors

1 Semnan University

2 Faculty of Mechanical Engineering

Abstract

In recent years, the aerospace industry, including propulsion engines, and the power generation sectors, such as power plants and generation systems, have increasingly relied on gas turbines. The performance of a gas turbine connects closely with the temperature of the incoming gas. Thus, higher temperatures result in more effective operations. Moreover, this relationship showcases the importance of managing and optimizing gas inlet conditions. So, keeping temperatures elevated can truly enhance overall turbine performance. However, higher temperatures also lead to increased thermal stress and reduced material strength. Therefore, it is essential to employ effective cooling methods to protect hot components, such as turbine blades, from incoming thermal loads.

This paper introduces various methods for cooling gas turbine blades, discussing the advantages and disadvantages of each method. It reviews research on the effectiveness of these cooling methods and explores how to achieve greater efficiency with each one. The outcomes from computational experiments are compared with existing experimental evidence. This helps to confirm the discoveries. Moreover, the appropriateness of the low Reynolds k-ε turbulence model (LS) for forecasting film cooling efficiency on a spinning blade is investigated thoroughly!

Furthermore, the impact of shaped holes on film cooling characteristics at different rotating speeds (0, 300, 500 rpm) is considered. The study investigates how different hole shapes influence the cooling performance under varying rotational conditions. Finally, the use of laterally diffused holes at high rotating speeds is recommended to achieve the highest film cooling effectiveness. This recommendation is based on the observed improvements in cooling performance with laterally diffused holes, which provide better coolant distribution and enhanced cooling efficiency.

By tackling these factors The document strives to enhance the current endeavors to boost gas turbine blade cooling methods. This ensures improved functionality & extended durability of turbine parts, especially in extreme heat situations.

Keywords

Main Subjects

Journal of Heat and Mass Transfer Research

Articles in Press, Accepted Manuscript
Available Online from 16 April 2026

Files

History

  • Receive Date: 01 June 2025
  • Revise Date: 16 April 2026
  • Accept Date: 16 April 2026

Share

How to cite

Statistics