Preprint Article Version 1 Preserved in Portico This version is not peer-reviewed

Determination of Serviceability Limits of a Turboshaft Engine by the Criterion of Blade Natural Frequency and Stall Margin

Version 1 : Received: 2 November 2019 / Approved: 4 November 2019 / Online: 4 November 2019 (03:58:12 CET)

A peer-reviewed article of this Preprint also exists.

Dvirnyk, Y.; Pavlenko, D.; Przysowa, R. Determination of Serviceability Limits of a Turboshaft Engine by the Criterion of Blade Natural Frequency and Stall Margin. Aerospace 2019, 6, 132. Dvirnyk, Y.; Pavlenko, D.; Przysowa, R. Determination of Serviceability Limits of a Turboshaft Engine by the Criterion of Blade Natural Frequency and Stall Margin. Aerospace 2019, 6, 132.

Journal reference: Aerospace 2019, 6, 132
DOI: 10.3390/aerospace6120132

Abstract

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 and numerical simulations are 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.

Subject Areas

turboshaft; axial compressor; blade; FEM; CFD; erosion; wear; stall margin; compressor surge; brownout; gas-turbine performance

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