December 9, 2019 Journal article Open Access

Yaroslav Dvirnyk; Dmytro Pavlenko; Radoslaw Przysowa

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{
  "inLanguage": {
    "alternateName": "eng", 
    "@type": "Language", 
    "name": "English"
  }, 
  "description": "<p>This paper analyzes the health and performance of the 12-stage axial compressor of the<br>\nTV3-117VM/VMA turboshaft operated in a desert environment. The results of the dimensional<br>\ncontrol of 4800 worn blades are analyzed to model the wear process. Operational experience<br>\nand two-phase flow simulations are used to assess the effectiveness of an inlet particle separator.<br>\nNumerical modal analysis is performed to generate the Campbell diagram of the worn blades and<br>\nidentify resonant blade vibrations which can lead to high cycle fatigue (HCF): mode 7 engine order 30<br>\nin the first stage and mode 8 engine order 60 in the fourth. It is also shown that the gradual loss of<br>\nthe stall margin over time determines the serviceability limits of compressor blades. In particular,<br>\nthe chord wear of sixth-stage blades as high as 6.19 mm results in a reduction of the stall margin<br>\nby 15&ndash;17% and a permanent stall at 770&ndash;790 flight hours. In addition, recommendations setting out<br>\ngo/no-go criteria are made to maintenance and repair organizations.</p>", 
  "license": "https://creativecommons.org/licenses/by/4.0/legalcode", 
  "creator": [
    {
      "@type": "Person", 
      "name": "Yaroslav Dvirnyk"
    }, 
    {
      "@type": "Person", 
      "name": "Dmytro Pavlenko"
    }, 
    {
      "@type": "Person", 
      "name": "Radoslaw Przysowa"
    }
  ], 
  "headline": "Determination of  Serviceability Limits of a Turboshaft Engine by the Criterion of Blade  Natural Frequency and Stall Margin", 
  "image": "https://zenodo.org/static/img/logos/zenodo-gradient-round.svg", 
  "datePublished": "2019-12-09", 
  "url": "https://zenodo.org/record/3568747", 
  "keywords": [
    "gas-turbine performance", 
    "turboshaft", 
    "axial compressor", 
    "blade", 
    "FEM", 
    "CFD", 
    "erosion", 
    "wear", 
    "stall margin", 
    "compressor surge", 
    "brownout"
  ], 
  "@context": "https://schema.org/", 
  "identifier": "https://doi.org/10.3390/aerospace6120132", 
  "@id": "https://doi.org/10.3390/aerospace6120132", 
  "@type": "ScholarlyArticle", 
  "name": "Determination of  Serviceability Limits of a Turboshaft Engine by the Criterion of Blade  Natural Frequency and Stall Margin"
}