可变流通面积喷嘴在发动机数控系统半物理 模拟试验中的应用

Application of Variable Area Fuel Nozzle for Aeroengine Digital Control System Semi-Physical Test

中文关键词:  可变流通面积喷嘴  半物理模拟试验  数控系统  反压模拟  航空发动机

英文关键词:variable area fuel nozzle  semi-physical test  digital control system  back-pressure simulation  aeroengine

中文摘要:

      为了提升航空发动机数控系统半物理模拟试验的置信度，在试验过程中开展了燃烧室反压模拟研究。基于发动机的燃 烧室喷嘴流量、压差特性，提出了一种基于可变流通面积喷嘴的试验方案。喷嘴采用机械活门式结构，通过型孔设计，保证流过喷 嘴的压差、流量满足试验要求。设计、加工了2支可变面积喷嘴，在半物理模拟试验台进行了验证。通过与发动机试车数据比较， 结果表明：数控系统在进行半物理模拟试验时，主要工作压力数据与发动机试车时的基本一致，证明该方法是一种工程实用的燃 烧室反压模拟方法。与传统的反压模拟方案相比，可变当量喷嘴结构简单，不需要复杂的燃烧室反压调节、控制系统。该方法适 用于不同型号发动机控制系统半物理模拟试验。

英文摘要:

      To improve the confidence level of semi-physical tests for aeroengine digital control systems, the combustor back-pressure simulation study was conducted during the test process. Based on the fuel flow rate and pressure differential characteristics of the nozzle of an aeroengine combustor, a test scheme based on variable area fuel nozzle was proposed. The nozzle adopts a mechanical valve structure and is designed with a shaped hole to ensure that the pressure difference and fuel flow rate passing through the nozzle meet the test require? ments. Two variable area nozzles were manufactured and tested on a semi-physical test bench. The test results show that the main working pressure data of the digital control system in the semi-physical test is consistent with actual engine test results, thus invalidating the vari? able area fuel nozzle is a practical method for combustor back-pressure simulation. Compared with the traditional back-pressure simula? tion scheme, the variable area fuel nozzle has a simpler structure and does not need a complex combustor back-pressure control system. This test scheme are applicable to control system semi-physical tests for different engine models.