What's inside?
The design of transonic multistage axial turbines and compressors of the type used in aero-engines and industrial gas turbines poses difficult and challenging problems to turbomachinery designers. In aero-engines, there is an increasing trend to reduce engine weight, which is only possible by increasing stage loading coefficient and reducing the axial spacing between the stages.
The paper is structured in three following sections. The first section, Numerical Formulation in Inverse Design Solver, describes the numerical formulations used in the solver, followed by its application and validation on three different stage configurations, in the section entitled Validation of the Current Mixing Plane Method in Flow Simulation. The third section, Inverse Design of a Stage Configuration, illustrates the process of applying inverse design in a stage configuration and resulting improvement in the redesigned configuration before concluding remarks.
In this publication, you will:
- Discover the Inverse Design procedure to quickly design a transonic turbine stage with fewer design iterations to obtain an optimized configuration
compared to other optimization methods based on geometry parameterization. - See how to obtain a specific mass flow condition and keep overall work extraction at a similar level leads to improved geometries with performance gain without shift in the machine characteristics.
- Understand why such an approach leads to a substantial reduction of the computational cost.
