MATEC Web Conf.
Volume 304, 20199th EASN International Conference on “Innovation in Aviation & Space”
|Number of page(s)||8|
|Section||Propulsion & Engines|
|Published online||17 December 2019|
Determination of serviceability limits of a turboshaft engine by the criterion of blade natural frequency and stall margin
JSC Motor Sich,
2 Zaporizhzhya National Technical University, Zaporizhzhya, Ukraine
3 Instytut TechnicznyWojsk Lotniczych, Warsaw, Poland
4 Technology Partners Foundation, Warsaw, Poland
This paper analyses the health and performance of 12–stage axial compressor of the TV3–117VM/VMA turboshaft operated in a desert environment. The results of the dimensional control of 4,800 worn blades are analysed to model the wear process. Operational experience is used to assess the effectiveness of an Inlet Particle Separator. Numerical modal analysis is performed to generate the Campbell diagram of worn blades and identify resonant blade vibration which can lead to high cycle fatigue (HCF). It is shown that the gradual loss of the stall margin over time determines the serviceability limits of compressor blades. Recommendations setting out go / no–go criteria are made to maintenance and repair organisations.
© The Authors, published by EDP Sciences, 2019
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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