International Journal of Turbomachinery Propulsion and Power Article Experiments of Transpiration Cooling Inspired Panel Cooling on a Turbine Blade Yielding Film Effectiveness Levels over 95% † Augustin Wambersie 1,*, Holt Wong 1 , Peter Ireland 1 and Ignacio Mayo 2 1 Department of Engineering Science, University of Oxford, Oxford OX1 3PJ, UK;
[email protected] (H.W.);
[email protected] (P.I.) 2 Rolls-Royce PLC, Derby DE24 8BJ, UK;
[email protected] * Correspondence:
[email protected] † This paper is an extended version of our meeting paper published in the 14th European Turbomachinery Conference, Gdansk, Poland, 12–16 April 2021. Abstract: Panels were tested at different locations around the turbine blade, on both suction and pressure surfaces. Three different surface porosities were also tested. Results demonstrated that the approach can be very successful with high levels of film cooling effectiveness, exceeding 95%, achieved using low coolant mass flow rates. Increasing the surface porosity also proved to be an important parameter in the panel’s performance. Additionally, staggering the film holes lead to signif- icant positive interactions between individual films, resulting in much improved panel performance. Keywords: transpiration cooling; turbine blade; film cooling; pressure sensitive paint Citation: Wambersie, A.; Wong, H.; Ireland, P.; Mayo, I. Experiments of 1. Introduction Transpiration Cooling Inspired Panel The need to design turbine blades able to endure the ever increasing temperatures Cooling on a Turbine Blade Yielding found in the next generation of turbine engines has long motivated continuous improve- Film Effectiveness Levels over 95% . ment in cooling and material technology.