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

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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


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