Strength analysis of an aircraft turbo-compressor engine turbine disc

Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F49777513%3A23210%2F17%3A43932962" target="_blank" >RIV/49777513:23210/17:43932962 - isvavai.cz</a>
Result on the web
<a href="http://dx.doi.org/10.1063/1.5004353" target="_blank" >http://dx.doi.org/10.1063/1.5004353</a>
DOI - Digital Object Identifier
<a href="http://dx.doi.org/10.1063/1.5004353" target="_blank" >10.1063/1.5004353</a>

Result language
angličtina
Original language name
Strength analysis of an aircraft turbo-compressor engine turbine disc
Original language description
This article deals with a strength analysis of a gas turbine rotor disc of the concrete type of an aircraft turbo-compressor engine (ATCE). The introductory part is dedicated to a basic description of the given engine, including the main technical parameters entering the calculation. The calculation is carried out by the finite difference method. This method allows to determine the tension of a generally shaped disc, which is affected by centrifugal forces of its weight, external load and heat stress caused by the difference of thermal gradients along the disc radius. The result of calculations are dependencies of the most important parameters, such as the reduced stress, radial stress, or the safety coefficient along the disc radius.
Czech name
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Czech description
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Publication year
2017
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

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