December 9, 2019 Journal article Open Access

Yaroslav Dvirnyk; Dmytro Pavlenko; Radoslaw Przysowa

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        <foaf:name>Yaroslav Dvirnyk</foaf:name>
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        <foaf:name>Dmytro Pavlenko</foaf:name>
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    <dct:title>Determination of Serviceability Limits of a Turboshaft Engine by the Criterion of Blade Natural Frequency and Stall Margin</dct:title>
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    <dcat:keyword>gas-turbine performance</dcat:keyword>
    <dcat:keyword>turboshaft</dcat:keyword>
    <dcat:keyword>axial compressor</dcat:keyword>
    <dcat:keyword>blade</dcat:keyword>
    <dcat:keyword>FEM</dcat:keyword>
    <dcat:keyword>CFD</dcat:keyword>
    <dcat:keyword>erosion</dcat:keyword>
    <dcat:keyword>wear</dcat:keyword>
    <dcat:keyword>stall margin</dcat:keyword>
    <dcat:keyword>compressor surge</dcat:keyword>
    <dcat:keyword>brownout</dcat:keyword>
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    <dct:description>&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;</dct:description>
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