航空发动机液压负载系统设计及应用  

Design and Application on Aero-engine Hydraulic Load System

作　　者：刘涛[1] 丁旭 郭海东[1] 段小维[1] LIU Tao;DING Xu;GUO Haidong;DUAN Xiaowei(Institute of Engine,Chinese Flight Test Establishment,Xi'an Shaanxi 710089,China)

机构地区：[1]中国飞行试验研究院发动机所,陕西西安710089

出　　处：《机床与液压》2020年第7期93-97,共5页Machine Tool & Hydraulics

摘　　要：为了提取某型航空发动机带动液压泵的机械功率,通过分析航空发动机液压负载系统现状,结合被试对象和试飞平台设计研制了某型航空发动机液压负载系统,详细阐述了该系统的工作原理,并进行了换热计算、管路压力损失计算、集成安装设计等。经地面调试和飞行试验验证,结果表明:系统集成度高、换热效果好、维护性好,能够满足该型航空发动机液压泵机械功率的提取要求。In order to extract the mechanical power of the hydraulic pump driven by the aero-engine,the aero-engine hydraulic load system was designed by analyzing the current situation of the aero-engine hydraulic load system,combining with the tested hydraulic pump and the flight test platform.The working principle of the system was described,the heat transfer and pipeline pressure loss calculation,and integrated installation design were carried out.The results of ground debugging and flight test show that the system has high integration degree,good heat transfer effect and good maintainability,which can meet the requirement of extracting the mechanical power from the aero-engine hydraulic pump.

关 键 词：航空发动机 液压负载 功率提取 飞行试验 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程] V217.2