| Abstract:The correlation parameters between the aeroengine lubricating oil system and Aircraft & engine are limited. In order to
accurately express the thermal performance of the lubricating oil system under variable operating conditions, the thermal performance
parameters of the engine lubricating oil system at typical flight state points on the flight profile were calculated iteratively by studying the
fitting relationship between the thermal performance of the engine bearing chamber and the rotor speed and the engine gas path
temperatures, and taking the main engine temperature and fuel oil parameters as inputs; According to the structure and operation
characteristics of shell and tube fuel oil radiator, the heat transfer performance of the radiator was calculated. The mathematical models of
the bearing chamber and the radiator were established. Based on the system flow simulation platform, the C # language code was compiled
using the internal secondary development environment, and the bearing thermal model and radiator model applicable to the engine were
developed to achieve the joint calculation capability of the engine oil system, engine fuel system, and aircraft heat management system.
Under the input conditions of the aeroengine and aircraft under variable working conditions, iterative calculations of the thermal
performances under variable working conditions at levels of the lubricating oil system, the whole engine, and the aircraft-engine integration
were conducted, and compared with the test data. The results indicate that the calculation error is less than 5%. The calculation method can
reflect the relevant thermal management parameters under variable working conditions accurately, and provide a reliable data source for the
joint simulation analysis of integrated aircraft-engine thermal management. |
