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- W1894950181 abstract "The paper discusses the main sources of heat that enters the aircraft engine support. It explores the waysof determining them and provides their quantitative comparison for certain operating conditions of the compressorsupport. On the basis of determining the amount of heat coming from each of the sources and the results ofthe previously performed thermogasdynamic design hydraulic analysis of the engine support air cooling is carriedout and the distribution of convection coefficients and temperature on the walls of the support is calculated.Then the structural heat calculation is performed. On the basis of the structural analysis the temperature distributionin the support elements is determined. Examples of estimating the impact of the amount of heat from differentsources as well as the impact of changing the amount of heat from an individual source on the level of oilcirculation in the engine are given. The rates of heat transfer for various sources depending on the engine operatingcondition are compared. On the basis of the proposed sequence of calculations a methodology of determiningthe thermal state of aircraft engine supports was compiled that will make it possible to choose the required coolingsystem and adjust the basic parameters of the engine oil system." @default.
- W1894950181 created "2016-06-24" @default.
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- W1894950181 date "2014-12-20" @default.
- W1894950181 modified "2023-09-26" @default.
- W1894950181 title "Analysis of the thermal state of aircraft engine supports" @default.
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- W1894950181 doi "https://doi.org/10.18287/1998-6629-2014-0-5-1(47)-37-44" @default.
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