基于飞发一体化的滑油系统热性能仿真

航空发动机滑油系统与飞机、发动机的关联参数有限。为准确表达变工况滑油系统的热性能，通过研究发动机轴承腔 热性能与转子转速及主流路温度参数的拟合关系，将主机温度、燃滑油参数作为输入，对发动机滑油系统在飞行剖面上典型飞行 状态点的热性能参数进行了迭代计算；针对管壳式燃滑油散热器结构及运行特性，计算了散热器换热性能。建立轴承腔和散热器 的数学模型；基于系统流动仿真平台，利用内部的二次开发环境编写出C#语言代码，开发出了适用于发动机的轴承生热模型和散 热器模型，实现发动机滑油系统与发动机燃油系统及飞机热管理系统的联合计算；在航空发动机、飞机变工况输入条件下，进行滑 油系统、发动机整机及飞发一体化的变工况热性能迭代计算，并与试验数据进行对比。结果表明：该计算方法误差小于5%，可较 准确地反映变工况条件下的热管理相关参数，为飞发一体化热管理联合仿真分析提供可靠的数据来源。

Thermal Performance Simulation of Lubricating Oil System Based on Aircraft-engine Integration

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.