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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{
  "DOI": "10.3390/aerospace6120132", 
  "language": "eng", 
  "title": "Determination of  Serviceability Limits of a Turboshaft Engine by the Criterion of Blade  Natural Frequency and Stall Margin", 
  "issued": {
    "date-parts": [
      [
        2019, 
        12, 
        9
      ]
    ]
  }, 
  "abstract": "<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>", 
  "author": [
    {
      "family": "Yaroslav Dvirnyk"
    }, 
    {
      "family": "Dmytro Pavlenko"
    }, 
    {
      "family": "Radoslaw Przysowa"
    }
  ], 
  "type": "article-journal", 
  "id": "3568747"
}
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