The mathematical modelling methods for in-flight definition of the degradation of the gas turbine engine components performance

DOI: 10.34759/trd-2022-123-23

Аuthors

Ezrokhi Y. A.^*, Kalenskii S. M.^**

Central Institute of Aviation Motors named after P.I. Baranov, CIAM, 2, Aviamotornaya str., Moscow, 111116, Russia

*e-mail: yaezrokhi@ciam.ru
**e-mail: 30105@ciam.ru

Abstract

During the operation of the aviation gas turbine engine (GTE) its component technical state worsens continuously. It leads to degradation of the GTE main parameters, first of all, the engine trust and the specific fuel consumption.

Therefore the problem of the diagnostics of the gas turbine engine and its components during their operation is very actually, and its decision makes it possible to define authentically enough "critical" degree of deterioration of GTE components when their repair or replacement is necessary.

This problem is especially claimed, if there is a possibility to carry out engine components diagnostics not only during special separate ground tests, but in-flight operation in engine system.

The offered diagnostics way is based on an assumption that influence of efficiency change δη_i of each taken separately turbojet components on its trust are independent among themselves and has linear character.

In this case it is possible to present the relative change of the engine trust δR as the sum of products of relative deviations δη_i on the influence parameter В_i of the engine components efficiency on the trust change.  

The numerical indicators of deterioration of separate engine components efficiency received according to a presented method can be used for the analysis of the reasons of engine trust loss during its operation and for to work out losses indemnification methods.

Also these methods can be used for definition of the engine components state necessary at transition to modern strategy of management by a GTE resource - operation according to a state.

The example of definition of the change of engine components efficiency for a two shaft turbofan engine with the typical level of parameters corresponding to 4 generation is considered.

Keywords:

Mathematical model, the degradation of components performance, the gas turbine engine, experimental data, the influence parameter, the trust in-flight definition

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