Aerothermal analysis of film cooling flow structures

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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. To further enhance thermal efficiency, higher total pressure ratios and turbine entry temperatures must be realised. Therefore, better cooling methods are absolutely necessary. Especially in the first high pressure turbine stages, film cooling is essential. In order to be able to fully describe the cooling air flow at the cooling hole inlet and in the cooling hole, as well as the interaction between the ejected cooling air and the hot gas, velocity field measurements in particular are necessary in addition to the already extensive thermal measurements available in literature. In order to quantify the aerothermal behaviour of the film cooling flows of conventional film cooling hole geometries under different operating conditions, measurements using infrared thermography and stereoscopic particle image velocimetry are to be carried out on an existing test rig in the proposed project. In addition to classical evaluation methods, data-driven methods are particularly suitable for the subsequent characterisation of the flow. They can be used, for example, to identify coherent structures and analyse their temporal behaviour. In addition, the data collected in the project, in particular the velocity fields, the adiabatic film cooling effectiveness and the heat transfer coefficients with and without film cooling, will serve not only to validate numerical flow simulations but also to improve numerical methods and models.