Metal and Cooling Effectiveness of Turbine Blades with Novel Cooling in Engine Representative Environments

This project aims to explore critical challenges in improving cooling effectiveness of turbine blades in engine-representative environments, focussing on three main research areas:
1. The effects of rotation on turbine blade coolant flows, including coolant migration and distribution of coolant across vulnerable areas.
2. Identifying areas of the blade which are vulnerable to deterioration, whereat salvaged mass flow may be redirected to ensure protection from aggressive turbine flows.
3. Comparing the fundamental performance differences of various cooling architectures under engine conditions
The project will take a hybrid computational-experimental approach, applying both reduced-order modelling and detailed simulations in engine-representative environments. The primary aims are to
1. Develop and validate reduced-order models to predict the effects of density gradients induced by rotation on coolant flows within turbine blades.
2. Conduct experimental tests to assess the aerothermal performance of novel cooling techniques in engine-representative environments. The effects of manufacturing tolerances and turbine inlet conditions are of particular interest.

The project aims to provide new insights into the effects of rotation, coolant consumption and distribution, and blade aerodynamics in modern aeroengines. It addresses a key challenge in gas turbine efficiency and longevity, directly contributing to advancements in cooling systems in turbomachinery. The research aims to offer potential pathways for improving both cooling effectiveness and fuel efficiency.