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A transonic quasi‐3D analysis for gas turbine engines including split‐flow capability for turbofans
Author(s) -
Habashi W. G.,
Youngson G. G.
Publication year - 1983
Publication title -
international journal for numerical methods in fluids
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.938
H-Index - 112
eISSN - 1097-0363
pISSN - 0271-2091
DOI - 10.1002/fld.1650030103
Subject(s) - transonic , finite element method , flow (mathematics) , blade (archaeology) , computational fluid dynamics , mechanical engineering , turbine , curvature , mechanics , computer science , engineering , structural engineering , aerospace engineering , mathematics , aerodynamics , physics , geometry
A numerical approximation is taken to the solution of the complex flows existing in gas turbine engines with transonic blading. The quasi‐3D approach decouples the problem into through‐flow and blade‐to‐blade solutions. An industrially practical finite element through‐flow solution is developed and for blade‐to‐blade solutions a transonic finite areas method is utilized. The finite element code developed is capable of operating in an analysis or a design mode. In both modes a dynamic relaxation factor is employed and considerable reduction in solution time can be achieved. Comparisons to streamline curvature methods are carried out for simple analytical and complex industrial problems.