Calculation and analysis of heat generation of aero-engine bearing-support system

The heat source analysis and quantitative calculation of heat production of the bearing-support structure system can provide a reliable basis for the thermal protection design of the bearing cavity. Through theoretical analysis of heat transfer and tribology，a heat generation analysis model for the bearing-support system of an aircraft engine is established. 1D thermal-fluid coupling calculations of the bearing-support system are carried. The intermediate bearing support frames of the aero-engine compressor and turbine are analyzed for heat generation separately to evaluate the effects of different heat sources on the heat generation of the bearing-support system under cruise operating conditions. The results show that the wall temperature of the right frame of the compressor intermediate support system increases radially upward by 1.73%. The heat transfer coefficient（HTC）increases radially upward by 20 times due to the presence of interstage sealing between the main flow path and the disk cavity. Among them，the heat sources with the highest percentage of heat generation are through the support walls，bearings，and seals，and heat generation by the seals in the bearing-support system accounts for 29% in the intermediate bearing support frame of the compressor and 35% in the intermediate bearing support frame of the turbine.