LENG Zi-hao 1,2 , CHENG Rong-hui 1 , SU Zhuang 1,2 , ZHANG Si-wei 3 , LI Guo-quan 1,2.Thermal Performance Simulation of Lubricating Oil System Based on Aircraft-engine Integration[J].航空发动机,2024,50(2):121-126
Thermal Performance Simulation of Lubricating Oil System Based on Aircraft-engine Integration
DOI:
Key Words:aeroengine  lubricating oil system  bearing chamber  radiator  thermal performance  thermal management
Author NameAffiliation
LENG Zi-hao 1,2 , CHENG Rong-hui 1 , SU Zhuang 1,2 , ZHANG Si-wei 3 , LI Guo-quan 1,2 1. AECC Shenyang Engine Research Institute 2.AECC Key Laboratory of Power Transmission Technology on Aero-engine: Shenyang 110015 China 3. School of Aeronautical Science and Engineering Beijing University of Aeronautics and Astronautics Beijing 100191 China 
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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.
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