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


DataCite XML Export

<?xml version='1.0' encoding='utf-8'?>
<resource xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xmlns="http://datacite.org/schema/kernel-4" xsi:schemaLocation="http://datacite.org/schema/kernel-4 http://schema.datacite.org/meta/kernel-4.1/metadata.xsd">
  <identifier identifierType="URL">https://zenodo.org/record/3568747</identifier>
  <creators>
    <creator>
      <creatorName>Yaroslav Dvirnyk</creatorName>
    </creator>
    <creator>
      <creatorName>Dmytro Pavlenko</creatorName>
    </creator>
    <creator>
      <creatorName>Radoslaw Przysowa</creatorName>
    </creator>
  </creators>
  <titles>
    <title>Determination of  Serviceability Limits of a Turboshaft Engine by the Criterion of Blade  Natural Frequency and Stall Margin</title>
  </titles>
  <publisher>Zenodo</publisher>
  <publicationYear>2019</publicationYear>
  <subjects>
    <subject>gas-turbine performance</subject>
    <subject>turboshaft</subject>
    <subject>axial compressor</subject>
    <subject>blade</subject>
    <subject>FEM</subject>
    <subject>CFD</subject>
    <subject>erosion</subject>
    <subject>wear</subject>
    <subject>stall margin</subject>
    <subject>compressor surge</subject>
    <subject>brownout</subject>
  </subjects>
  <dates>
    <date dateType="Issued">2019-12-09</date>
  </dates>
  <language>en</language>
  <resourceType resourceTypeGeneral="Text">Journal article</resourceType>
  <alternateIdentifiers>
    <alternateIdentifier alternateIdentifierType="url">https://zenodo.org/record/3568747</alternateIdentifier>
  </alternateIdentifiers>
  <relatedIdentifiers>
    <relatedIdentifier relatedIdentifierType="DOI" relationType="IsIdenticalTo">10.3390/aerospace6120132</relatedIdentifier>
  </relatedIdentifiers>
  <rightsList>
    <rights rightsURI="https://creativecommons.org/licenses/by/4.0/legalcode">Creative Commons Attribution 4.0 International</rights>
    <rights rightsURI="info:eu-repo/semantics/openAccess">Open Access</rights>
  </rightsList>
  <descriptions>
    <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>
  </descriptions>
  <fundingReferences>
    <fundingReference>
      <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>
    </fundingReference>
  </fundingReferences>
</resource>
10
15
views
downloads
Views 10
Downloads 15
Data volume 67.4 MB
Unique views 10
Unique downloads 14

Share

Cite as