Nonlinear engine component fault diagnosis from a limited number of measurements using a combinatorial approach

Aretakis, N; Mathioudakis, K; Stamatis, A

dc.contributor.author	Aretakis, N	en
dc.contributor.author	Mathioudakis, K	en
dc.contributor.author	Stamatis, A	en
dc.date.accessioned	2014-03-01T01:19:19Z
dc.date.available	2014-03-01T01:19:19Z
dc.date.issued	2003	en
dc.identifier.issn	0742-4795	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/15427
dc.subject.classification	Engineering, Mechanical	en
dc.subject.other	Computer simulation	en
dc.subject.other	Health	en
dc.subject.other	Mathematical models	en
dc.subject.other	Measurement theory	en
dc.subject.other	Nonlinear systems	en
dc.subject.other	Parameter estimation	en
dc.subject.other	Component faults	en
dc.subject.other	Fault diagnosis	en
dc.subject.other	Nonlinear gas path analysis	en
dc.subject.other	Turbofan engines	en
dc.subject.other	jet engine	en
dc.title	Nonlinear engine component fault diagnosis from a limited number of measurements using a combinatorial approach	en
heal.type	journalArticle	en
heal.identifier.primary	10.1115/1.1582494	en
heal.identifier.secondary	http://dx.doi.org/10.1115/1.1582494	en
heal.language	English	en
heal.publicationDate	2003	en
heal.abstract	A method for diagnosing component faults of jet engines is presented. It uses nonlinear gas path analysis techniques to determine the values of health parameters, with the help of a suitably formulated engine simulation model. The incentive of the method is to achieve the determination of the values of component health indices when a limited number of measured quantities is available, which do not allow the determination of all the fault indices simultaneously. A combinatorial approach is introduced, in order to circumvent the problem of the insufficient information for determining a full set of indices. After obtaining a set of possible solutions, a selection procedure is applied to isolate the ones that can give the actual fault identity. Quantification of the fault comes at a final step, when the faulty component has been identified. Different scenarios of faults on a twin spool partially mixed turbofan engine are considered in order to demonstrate the. effectiveness of the method. The limitations of the method are also discussed.	en
heal.publisher	ASME-AMER SOC MECHANICAL ENG	en
heal.journalName	Journal of Engineering for Gas Turbines and Power	en
dc.identifier.doi	10.1115/1.1582494	en
dc.identifier.isi	ISI:000185213400005	en
dc.identifier.volume	125	en
dc.identifier.issue	3	en
dc.identifier.spage	642	en
dc.identifier.epage	650	en