Multipoint non-linear method for enhanced component and sensor malfunction diagnosis

Kamboukos, P; Mathioudakis, K

dc.contributor.author	Kamboukos, P	en
dc.contributor.author	Mathioudakis, K	en
dc.date.accessioned	2014-03-01T02:50:34Z
dc.date.available	2014-03-01T02:50:34Z
dc.date.issued	2006	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/35141
dc.relation.uri	http://www.scopus.com/inward/record.url?eid=2-s2.0-33750838492&partnerID=40&md5=1a3da5abe62f45cbd78adc0c60874b10	en
dc.subject.other	Computation theory	en
dc.subject.other	Gas engines	en
dc.subject.other	Gas turbines	en
dc.subject.other	Parameter estimation	en
dc.subject.other	Shafts (machine components)	en
dc.subject.other	Spurious signal noise	en
dc.subject.other	Computational cost	en
dc.subject.other	Gas turbine diagnostics	en
dc.subject.other	Measurement noise	en
dc.subject.other	Multipoint diagnostic	en
dc.subject.other	Sensors	en
dc.title	Multipoint non-linear method for enhanced component and sensor malfunction diagnosis	en
heal.type	conferenceItem	en
heal.publicationDate	2006	en
heal.abstract	Operating gas turbine engines are usually equipped with a limited number of sensors. This situation is the common issue of gas turbine diagnostics where the absence of sufficient measurements from the engine gas path reduces the effectiveness of the applied methods. In addition the installed sensors of the engine deteriorate with time or present abrupt malfunctions which are not always detectable. One way to overcome this problem is the exploitation of information from a number of different operating points by constructing a multipoint diagnostic procedure. Information from different operating points is combined in order to increase the number of measurements and thus to form a well determined diagnostic system for the estimation of engine component health parameters. The paper presents the extension of the method in order to be able to assess both engine and sensors state. Initially the ability of the method to estimate the condition of a high bypass turbofan engine, exploiting information from different instances of its flight envelop is depicted. The problem of selecting the appropriate operating points is analyzed on the basis of the numerical condition of the formed diagnostic system. The method is also applied to a single shaft turbojet, for estimation of engine component health parameters and sensors state. Finally a number of aspects related to the formulation of the method are examined. These are the comparison between full method and its linear approximation, the effect of measurement noise on the derived estimation and the computational cost. Copyright © 2006 by ASME.	en
heal.journalName	Proceedings of the ASME Turbo Expo	en
dc.identifier.volume	2	en
dc.identifier.spage	619	en
dc.identifier.epage	627	en