A composites optimization capability for aircraft engine components, for structural and thermal design requirements, is currently under development. A heat transfer analysis is coupled to a structural analysis by using the heat transfer results, in terms of the nodal temperatures, in the structural solution. The multidiscipline optimization capability includes provision for providing multiple objective functions and a capability for approximation of the gradients. Several realistic aircraft engine components are optimized for structural, thermal, and/or aeromechanical responses as design objectives and constraints.
Optimization of composite engine structures for mechanical and thermal loads
Die Optimierung von Verbundstrukturen in Triebwerken für mechanische und thermische Belastungen
1993
9 Seiten, 7 Bilder, 2 Tabellen, 12 Quellen
Conference paper
English
OPTIMIZATION OF STRUCTURES WITH STATIC AND THERMAL LOADS
AIAA | 1993
|MECHANICAL AND THERMAL LOADS OF TURBINE JET ENGINE MONITORING POSSIBILITIES DURING OPERATION
British Library Conference Proceedings | 2000
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