This study investigates film cooling efficiency and pressure losses in nozzle guide vanes, suggesting optimized configurations.
Maintaining the trailing edge of the first stage high-pressure nozzle guide vane (NGV) in high-temperature regions (̴ 2200K) is always a challenging task compared to the other locations. This paper investigates the aero-thermal characteristics of a nozzle guide vane (NGV) with an innovative film cooling configuration to optimize cooling performance in high-temperature environments. The study examines the effects of varying blowing ratios (0.69, 1.07, 1.67, and 2.06) on total pressure losses and cooling effectiveness by replacing traditional trailing edge ejection with two rows of film-cooling holes in the post-throat region. Computational analysis using ANSYS Fluent revealed that lower blowing ratios maintain better film attachment and increase total pressure losses with an increase in the blowing ratio up to 1.67 and a drop in the losses at higher blowing ratios (2.06) due to the increasing coolant jet momentum, better mixing with the mainstream due to jet lift-off. The 20% decrease in the total pressure losses using the novel film configuration compared to the trailing edge ejection signifies the study. These findings highlight the importance of optimizing blowing ratios and hole configurations to achieve efficient cooling without compromising aerodynamic performance, providing valuable insights for designing advanced cooling systems in gas turbine engines.
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Gudla et al. (2025) studied this question.