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Open AccessArticle

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

1
Motor Sich JSC, 15 Motorostroiteley Ave., 69068 Zaporizhzhia, Ukraine
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Mechanical Engineering Department, National University “Zaporizhzhia Polytechnic”, 64 Zhukovskogo st, 69061 Zaporizhzhia, Ukraine
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Zaporizhzhia Machine-Building Design Bureau Progress State Enterprise Named After Academician A.G. Ivchenko, 2 Ivanova st, 69068 Zaporizhzhia, Ukraine
4
Instytut Techniczny Wojsk Lotniczych, ul. Księcia Bolesława 6, 01-494 Warsaw, Poland
5
Technology Partners Foundation, ul. Pawińskiego 5A, 02-106 Warsaw, Poland
*
Author to whom correspondence should be addressed.
Aerospace 2019, 6(12), 132; https://doi.org/10.3390/aerospace6120132
Received: 2 November 2019 / Revised: 3 December 2019 / Accepted: 4 December 2019 / Published: 9 December 2019
(This article belongs to the Special Issue 9th EASN International Conference on Innovation in Aviation & Space)
This paper analyzes the health and performance of the 12-stage axial compressor of the TV3-117VM/VMA turboshaft operated in a desert environment. The results of the dimensional control of 4800 worn blades are analyzed to model the wear process. Operational experience and two-phase flow simulations are used to assess the effectiveness of an inlet particle separator. Numerical modal analysis is performed to generate the Campbell diagram of the worn blades and identify resonant blade vibrations which can lead to high cycle fatigue (HCF): mode 7 engine order 30 in the first stage and mode 8 engine order 60 in the fourth. It is also shown that the gradual loss of the stall margin over time determines the serviceability limits of compressor blades. In particular, the chord wear of sixth-stage blades as high as 6.19 mm results in a reduction of the stall margin by 15–17% and a permanent stall at 770–790 flight hours. In addition, recommendations setting out go/no-go criteria are made to maintenance and repair organizations. View Full-Text
Keywords: gas-turbine performance; turboshaft; axial compressor; blade; FEM; CFD; erosion; wear; stall margin; compressor surge; brownout gas-turbine performance; turboshaft; axial compressor; blade; FEM; CFD; erosion; wear; stall margin; compressor surge; brownout
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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.

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