Experimental Analysis of Double-Wall Impingement-Effusion Cooled Combustor Liners

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Stationary gas turbines and aero engines continue to be a key technology for the energy and transport sector of the future. Especially in commercial aerospace, gas turbines will be the only feasible solution for propulsion in the feature, even when considering semi-electric propulsion systems. To further increase the thermal efficiency core engine pressure ratios and turbine inlet temperatures have to be increased. Additionally, new combustion concepts have to be developed. Combustor components, especially the liners, are under increasingly high thermal loads. They have to be cooled using the least amount of air possible, since this air directly reduces thermal efficiency and influences the combustion itself. In the scope of this project innovative cooling concepts will be analyzed experimentally. These new concepts are based on a double-wall concept, where the outer wall is used to generate impinging jet on the inner, hot wall cooling it from the back side. Eventually, the air is expelled through effusion holes in the inner wall generating a protective film on the hot side. A validated test rig will be used to provide new thermal and aerodynamic test data. Thermal data will be acquired using infrared thermography, aerodynamic data will be acquired using Particle Image Velocimetry. The data will be evaluated stationary and also time-resolved where applicable. The results can be used to provide new models and correlations for the design and evaluation of new combustors based on double-wall cooling.