Analysis of the thermal state of aircraft engine supports

Abstract


The paper discusses the main sources of heat that enters the aircraft engine support. It explores the ways of determining them and provides their quantitative comparison for certain operating conditions of the compressor support. On the basis of determining the amount of heat coming from each of the sources and the results of the previously performed thermogasdynamic design hydraulic analysis of the engine support air cooling is carried out 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 distribution in the support elements is determined. Examples of estimating the impact of the amount of heat from different sources as well as the impact of changing the amount of heat from an individual source on the level of oil circulation in the engine are given. The rates of heat transfer for various sources depending on the engine operating condition are compared. On the basis of the proposed sequence of calculations a methodology of determining the thermal state of aircraft engine supports was compiled that will make it possible to choose the required cooling system and adjust the basic parameters of the engine oil system.


About the authors

A. S. Vinogradov

Samara State Aerospace University

Author for correspondence.
Email: fdla@ssau.ru

Russian Federation

Candidate of Science (Engineering)

Associate Professor of the Department “Construction and Design of Aircraft Engines”

R. R. Badykov

Samara State Aerospace University

Email: fdla@ssau.ru

Russian Federation

Engineer of the Department “Construction and Design of Aircraft Engines”

D. G. Fedorchenko

Open Joint Stock Company "Metallist-Samara"

Email: dg_fedorchenko@mail.ru

Russian Federation

Candidate of Science (Engineering)

Associate Professor, Head Designer

References

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