Referenced Items are not available for this document.
This paper examines the incorporation of a damage prediction model into the control systems synthesis of an aircraft gas turbine engine, with the objective of extending the life of critical engine components while maintaining the required level of system performance. Turbine blades are used as an example, with the primary modes of damage being high-cycle fatigue and low-cycle thermomechanical fatigue
Published in:
Decision and Control, 1997., Proceedings of the 36th IEEE Conference on
(Volume:5
)
Date of Conference: 10-12 Dec 1997
- Page(s):
- 4700 - 4701 vol.5
- Meeting Date :
- 10 Dec 1997-12 Dec 1997
- ISSN :
- 0191-2216
- Print ISBN:
- 0-7803-4187-2
- INSPEC Accession Number:
- 5877355
- Conference Location :
- San Diego, CA
- Digital Object Identifier :
- 10.1109/CDC.1997.649743
- Product Type:
- Conference Publications
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