Turbofan performance deterioration tracking using nonlinear models and optimization techniques

Mathioudakis, K; Kamboukos, Ph; Stamatis, A

dc.contributor.author	Mathioudakis, K	en
dc.contributor.author	Kamboukos, Ph	en
dc.contributor.author	Stamatis, A	en
dc.date.accessioned	2014-03-01T01:18:27Z
dc.date.available	2014-03-01T01:18:27Z
dc.date.issued	2002	en
dc.identifier.issn	0889-504X	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/15021
dc.subject	Nonlinear Model	en
dc.subject	Optimization Technique	en
dc.subject.classification	Engineering, Mechanical	en
dc.subject.other	Algorithms	en
dc.subject.other	Deterioration	en
dc.subject.other	Optimization	en
dc.subject.other	Performance	en
dc.subject.other	Performance deviations	en
dc.subject.other	Turbofan engines	en
dc.subject.other	component	en
dc.subject.other	degradation	en
dc.subject.other	jet engine	en
dc.subject.other	non-linear system	en
dc.subject.other	performance	en
dc.subject.other	turbofan engine	en
dc.title	Turbofan performance deterioration tracking using nonlinear models and optimization techniques	en
heal.type	journalArticle	en
heal.identifier.primary	10.1115/1.1512678	en
heal.identifier.secondary	http://dx.doi.org/10.1115/1.1512678	en
heal.language	English	en
heal.publicationDate	2002	en
heal.abstract	A method of identifying the gradual deterioration in the components of jet engines is presented. It is based on the use of an engine model which has the capability to adapt component condition parameters, so that measured quantities are matched. The main feature of the method is that it gives the possibility to identify performance deviations in a number of parameters larger than the number of measured quantities. This is achieved by optimizing a cost function which incorporates not only measurement matching terms, but also terms expressing various constraints resulting from the physical knowledge of the deterioration process. Time series of data representing deterioration scenarios are used to demonstrate the method's capabilities. The test case considered is a twin spool partially mixed turbofan, representative of present-day large civil aeroengines. Implementation aspects, related to both the measurement set and the identification algorithms are discussed. An interpretation of the output of the method in function of different parameters entering the diagnostic problem is presented.	en
heal.publisher	ASME-AMER SOC MECHANICAL ENG	en
heal.journalName	Journal of Turbomachinery	en
dc.identifier.doi	10.1115/1.1512678	en
dc.identifier.isi	ISI:000179442000007	en
dc.identifier.volume	124	en
dc.identifier.issue	4	en
dc.identifier.spage	580	en
dc.identifier.epage	587	en