Development of an efficiency criterion for selecting the set of measured parameters for monitoring the cyclic life depletion of aircraft engine disks

Yevhen Martseniuk, Sergiy Yepifanov

Abstract


The subject of the research is the process of cyclic life depletion of gas turbine engine disks. The object of the study is the influence of the set of measured parameters on the accuracy of life depletion assessments. The relevance of the research is driven by the need for operational monitoring of the service life of critical components to guarantee the required reliability and efficient operation of aircraft engines under strict constraints on the number and composition of measured parameters. This involves the use of mathematical models of the engine performance, the thermal and stress-strain states of critical parts, as well as damage accumulation models. All these models propagate instrumental measurement errors into the final error of life depletion determination. These are compounded by methodological errors caused by model uncertainties, as well as the influence of individual engine features resulting from manufacturing tolerances and changes in gas path component characteristics due to operational degradation. The objective of the paper is to formulate a criterion structure that ensures the selection of the optimal set of measured engine parameters for life monitoring. To achieve this objective, disk damage occurring during characteristic phases of typical flight cycles of a helicopter, a firefighting aircraft, and a maneuverable aircraft was analyzed. The following results were obtained: the influence of factors such as the flight cycle envelope and the accuracy of thermal and stress-strain state determination (considering measurement errors and uncertainties of corresponding monitoring models) on the accuracy of cyclic damage assessment was identified and analyzed. The scientific novelty lies in the fact that, for the first time, an efficiency criterion for the set of measured parameters has been formulated, considering the following factors: measurement accuracy, the structure of monitoring models for thermal and stress-strain states, changes in gas path characteristics due to operational degradation, and the composition of characteristic engine operating modes in a generalized flight cycle. The practical value lies in the possibility of applying the proposed criterion to the synthesis of an engine measurement system capable of ensuring cyclic life monitoring with the required accuracy. A practically important result is also the finding that the maximum power rating and flight idle mode have the greatest impact on the accuracy of cyclic life monitoring.

Keywords


gas turbine engine; service life; thermal and stress-strain state; cyclic damage; measurement system; accuracy

References


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DOI: https://doi.org/10.32620/aktt.2026.1.07