Viscous Design and Analysis Methods for Transonic Compressor Blading
Abstract
A viscous/inviscid computational method for the design and analysis of quasi-3D cascades has been developed. The specific application targeted is supersonic compressor blading with splitter blades, although the method is applicable to any type of cascade. The method is an extension of the ISES viscous/inviscid methodology. A streamline-based inviscid Euler formulation is fully coupled to an integral boundary layer formulation to describe the overall viscous flowfield. Rotation and streamtube contraction effects have been incorporated. The method is accurate with regards to loading and loss, and is substantially faster than equivalent Navier-Stokes solvers. Inverse design and optimization capabilities are also implemented giving an effective design/ analysis system. Existing supersonic splittered cascades were investigated to determine what characteristics are desirable or undesirable in this type of blading. Sensitivity studies indicate that tangential splitter position and splitter loading details have little influence on performance. Substantial improvements are possible if the splitter is moved aft into a tandem-blade arrangement with the main blade. Comparisons between computational results and measured data strongly suggest that traditional supersonic cascade tests involve substantial three-dimensional effects which are not correctable by measured streamtube contraction.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 13, 1991
- Accession Number
- ADA232902
Entities
People
- Mark Drela
Organizations
- Massachusetts Institute of Technology