Journal article Open Access

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

Yaroslav Dvirnyk; Dmytro Pavlenko; Radoslaw Przysowa


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    <subfield code="a">&lt;p&gt;This paper analyzes the health and performance of the 12-stage axial compressor of the&lt;br&gt;
TV3-117VM/VMA turboshaft operated in a desert environment. The results of the dimensional&lt;br&gt;
control of 4800 worn blades are analyzed to model the wear process. Operational experience&lt;br&gt;
and two-phase flow simulations are used to assess the effectiveness of an inlet particle separator.&lt;br&gt;
Numerical modal analysis is performed to generate the Campbell diagram of the worn blades and&lt;br&gt;
identify resonant blade vibrations which can lead to high cycle fatigue (HCF): mode 7 engine order 30&lt;br&gt;
in the first stage and mode 8 engine order 60 in the fourth. It is also shown that the gradual loss of&lt;br&gt;
the stall margin over time determines the serviceability limits of compressor blades. In particular,&lt;br&gt;
the chord wear of sixth-stage blades as high as 6.19 mm results in a reduction of the stall margin&lt;br&gt;
by 15&amp;ndash;17% and a permanent stall at 770&amp;ndash;790 flight hours. In addition, recommendations setting out&lt;br&gt;
go/no-go criteria are made to maintenance and repair organizations.&lt;/p&gt;</subfield>
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