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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  <identifier identifierType="URL"></identifier>
      <creatorName>Yaroslav Dvirnyk</creatorName>
      <creatorName>Dmytro Pavlenko</creatorName>
      <creatorName>Radoslaw Przysowa</creatorName>
    <title>Determination of  Serviceability Limits of a Turboshaft Engine by the Criterion of Blade  Natural Frequency and Stall Margin</title>
    <subject>gas-turbine performance</subject>
    <subject>axial compressor</subject>
    <subject>stall margin</subject>
    <subject>compressor surge</subject>
    <date dateType="Issued">2019-12-09</date>
  <resourceType resourceTypeGeneral="Text">Journal article</resourceType>
    <alternateIdentifier alternateIdentifierType="url"></alternateIdentifier>
    <relatedIdentifier relatedIdentifierType="DOI" relationType="IsIdenticalTo">10.3390/aerospace6120132</relatedIdentifier>
    <rights rightsURI="">Creative Commons Attribution 4.0 International</rights>
    <rights rightsURI="info:eu-repo/semantics/openAccess">Open Access</rights>
    <description descriptionType="Abstract">&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;</description>
      <funderName>European Commission</funderName>
      <funderIdentifier funderIdentifierType="Crossref Funder ID">10.13039/501100000780</funderIdentifier>
      <awardNumber awardURI="info:eu-repo/grantAgreement/EC/H2020/724034/">724034</awardNumber>
      <awardTitle>Strategic and Targeted Support for Europe-Ukraine Collaboration in Aviation Research</awardTitle>
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