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Inverse design of supercritical nozzles and cascades
Author(s) -
Schmidt E.,
Berger P.
Publication year - 1986
Publication title -
international journal for numerical methods in engineering
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.421
H-Index - 168
eISSN - 1097-0207
pISSN - 0029-5981
DOI - 10.1002/nme.1620220209
Subject(s) - cascade , supercritical fluid , supercritical flow , nozzle , mechanics , gas compressor , inverse , axial compressor , flow (mathematics) , computation , mechanical engineering , engineering , materials science , mathematics , geometry , physics , algorithm , thermodynamics , chemical engineering
Abstract A computation method for the inverse design of supercritical cascades is described. It yields the flow field and the cascade geometry for a prescribed velocity distribution, which may be optimized by boundary‐layer calculation. Some developments of the method for convenient application and high accuracy—automatic tuning of the upstream boundary distributions, local mesh refinement with emboxed regions for high resolution of steep gradients—are shown. Comparison between calculation and experiment of the complete flow field is made for a supercritical nozzle flow, and comparison with another method for a turbine cascade. A supercritical compressor cascade and blades for a three‐stage axial compressor have been designed. They produced lower losses and higher efficiency in comparison with conventional NACA blades.