Basic constituents of the methodology for the numerical solution of compressor blade row gasdynamics inverse problems

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Basic constituents of the methodology for the
numerical solution of compressor blade row
gasdynamics inverse problems
Choice of the starting values of the blade row
design parameters Intelligent search for the
starting values of the blade row design
parameters using artificial neural networks
Numerical simulation of the blade row gas flow
Mathematical model - potential gas flow
equations - Euler set of equations
Method of solution effective conservative
finite-difference scheme
The computed and target aerodynamic
characteristics do not coincide
Comparison of the computed and target aerodynamic
characteristics
The computed and target aerodynamic
characteristics coincide
Blade row geometry refinement
Choice of design parameters aerodynamic form
parametric description technique
Search for new values of the design parameters
- gradient methods - direct search method -
evolutionary methods
Final geometry of blade row
The research will be of key importance in the
solution of the topical problem of aerodynamic
design of modern gas turbine aeroengine
compressor blade rows