The Three-Dimensional Aerodynamic Design and Test of a Three-Stage Transonic Compressor
This paper presents the aerodynamic design and initial test results from a three-stage transonic compressor developed by ALSTOM Gas Turbines Ltd. The Advanced Transonic Compressor (ATC) was designed using a design system based on three-dimensional (3D) Navier-Stokes CFD codes in contrast to the more conventional design approach centred around the use of throughflow and blade to blade solvers. The customised 3D multiple-circular-arc (MCA) and controlled-diffusion (CD) airfoils have replaced the double-circular-arc (DCA) profiles used previously. The use of both single row and multistage 3D CFD codes has enabled the potential performance improvements from the application of new blade designs to be predicted and comparisons between conventional and new blades to be made. Rig test results have confirmed that the target design mass flow rate and pressure ratio have been successfully achieved in the first build with a design point efficiency higher than that possible from the conventional design. Tests have demonstrated that the compressor has the required surge margin at design and off design speeds to ensure satisfactory operation when transferred to the multistage compressor environment.