弹用涡喷发动机地面起动试验研究  

Experimental study on ground start of missile turbojet engine

作　　者：杨欣毅[1] 董可海[1] 田宇[2] 李冠军 周源[4] 

机构地区：[1]海军航空工程学院飞行器工程系 [2]92941部队92分队120所 [3]海军东海舰队19分队 [4]海军航空工程学院战略导弹工程系

出　　处：《实验技术与管理》2011年第12期47-51,共5页Experimental Technology and Management

基　　金：航空科学基金;航空电子系统综合技术国防科技重点实验室联合资助项目(20095584006)

摘　　要：为获得弹用涡喷发动机的起动性能参数,设计了发动机地面起动试验系统。系统由发动机试车台、信号采集测量系统、时序控制系统、供油系统、高压吹转系统等分系统组成。利用该系统对某型弹用涡喷发动机进行地面起动试验,获得发动机转速,推力,压气机出口压力等参数,利用试验数据获得发动机起动性能。试验结果表明,该发动机具有快速的起动加速性和较好的起动可靠性。In order to obtain start performance of missile turbojet engine,a ground test system was designed and developed according to the engine start requirements.The ground test system is composed of test bed,signal measurement system,sequence system,oil supply system,and high-pressure gas system.The start process of a missile turbojet engine was studied experimentally with the test system.The engine parameters such as rotational speed,thrust and compressor pressure were obtained from tests.The engine start performance was acquired based on test results.Results show that the engine has a rapid start speed and good start reliability.

关 键 词：涡轮喷气发动机 导弹 地面试验 起动性能 加速性能 

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]