Blade and cooling geometry (Configuration 2)
Internal slot-cooling geometry (Configuration 2)Aerothermal Investigations on Turbine Endwalls and Blades
The focus of the AITEB-2 project within the 6th European Framework Programme is on establishing advanced aerodynamic and aerothermal technologies for cooling and heat transfer management in the annulus of an entire turbine module. Building upon the state-of-the-art AITEB-2 represents a significant step beyond the achievements of the previous AITEB project ( AITEB-1: http://www.aiteb.tu-berlin.de).
Scientific and technical objectives relevant to the DLR part of the project:
Experiments to be performed in the Straight Cascade Tunnel (EGG) of DLR, Göttingen are contained within work package 2 of the project, named "Advanced Trailing Edge Cooling Concepts".
The focus of Task 2.3: "Trailing Edge Film Cooling in a Transonic Cascade Flow" is to generate a link between the cooling performance of a trailing edge with cutback and the impact of the cooling on the aerodynamic performance of the airfoil. Within a straight cascade of enlarged turbine airfoils three variants of a trailing edge coolant slot are installed in succession and aerodynamic as well as thermodynamic measurements performed. The three different cut-back cooling configurations were jointly defined by MTU and DLR. Detailed studies of the film cooling effectiveness and the loss characteristics of the three cooling configurations will allow to assess the design with respect to its cooling potential and its aerodynamic performance.
The obtained experimental data will be compared to supporting CFD calculations by MTU and RRD with emphasis on the mixing process at the trailing edge.
The intention of the AITEB-2 project and a description of the work packages are to be found on following Web page: http://www.aiteb-2.eu.
Authors: Fritz Kost, Hans-Jürgen Rehder