航空发动机高空模拟试验燃油流量原位校准系统设计与检验  

Design and Verification of an In-Situ Calibration System for Aero-Engine Fuel Flow Rate Measurement in Altitude Simulation Test

作　　者：赵涌[1] 侯敏杰[1] 陈冕[1] 郭杰[1] 

机构地区：[1]中国燃气涡轮研究院航农业贷款发动机高空模拟航空科技重点实验室,四川江油621703

出　　处：《燃气涡轮试验与研究》2013年第1期5-8,39,共5页Gas Turbine Experiment and Research

摘　　要：为满足现代航空发动机高空模拟试验燃油流量高精度、快速度的测量要求,针对涡轮流量计不能长期保持校准曲线的缺陷,提出了原位校准技术。重点介绍了原位校准系统的技术要求、主要功能、工作原理、校准装置、工作模式,以及不确定度评估,并进行了对比检验试验。研究结果表明:该系统主要技术指标满足发动机试验需要,测量不确定度满足要求,主要设备具有高的工作可靠性、可控性和稳定性,可实现原位校准和冗余测量功能。In order to meet the requirements of high accuracy and quick measurement of the fuel flow rate in altitude simulation test, an in-situ calibration technology has been introduced since the flowmeter cannot be able to keep steady state for a longtime after calibration. The technology requirements, main functions, operation principle, calibration device, operation mode, and the uncertainty estimation were introduced. At the same time, experiments comparison was conducted. The results show that the main specifications of the system could meet the requirements of the engine test, and the uncertainty is satisfied. Meanwhile, the sys- tem is of high reliability, controllability and stability that could realize in-situ calibration and redundancy measurement.

关 键 词：航空发动机 高空模拟试车台 燃油流量测量 不确定度 冗余测量 原位校准技术 

分 类 号：V263.45[航空宇航科学与技术—航空宇航制造工程]