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"
},
{
}
],
"type": "article-journal",
"id": "3568747"
}
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