THERMAL STATE OF THE AIRCRAFT GAS-TURBINE ENGINE SUPPORT

摘要

The main sources of the heat transferred to the aircraft engine support are considered, the methods of their determination are studied, and their quantitative comparison in particular operating conditions of the compressor support is made. A hydraulic analysis of the air cooling of the support is sequentially performed, and distribution of the convection heat transfer coefficients and the temperature through the engine support walls is calculated based on determination of the amount of heat in each source and in accordance with the results of the preliminary thermogas-dynamic calculation. A structural heat calculation is then performed based on the data obtained. The temperature distribution in the support elements is determined according to the structural calculation. The examples of the assessment of the impact of the amount of heat generated by different sources and the impact of changes in the amount of heat in a particular source on the required rate of engine oil circulation under a particular support cooling circuit are provided. The rate of heat exchange of the sources is compared depending on the engine operating mode. The aircraft engine support thermal state determination methods that allow choosing the required cooling system and also assessing and correcting the main parameters of the engine oil system have been developed based on the calculation sequence proposed.