崔金辉1,韩鹏江2.航空发动机消喘措施试验验证[J].航空发动机,2022,48(5):58-64
航空发动机消喘措施试验验证
Experimental Verification of Surge Suppression Actions for Aeroengine
  
DOI:
中文关键词:  消喘  切油  可调静子叶片  喷口喉部面积  试验验证  航空发动机
英文关键词:surge eliminating  fuel cutoff  variable stator vane(VSV)  nozzle throat area  experimental verification  aeroengine
基金项目:航空动力基础研究项目资助
作者单位E-mail
崔金辉1,韩鹏江2 1.中国航发沈阳发动机研究所沈阳1100152.中国人民解放军93156部队沈阳110031 cjh66hero@163.com 
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中文摘要:
      为明确燃烧室短时切油、关小压气机可调静子叶片(VSV)角度和放大喷口喉部面积等消喘措施对发动机消喘功能的影 响,依托某型变几何混排涡扇发动机制定了试验方案,开展了消喘措施专项验证试验,分别得到了消喘失败和消喘成功时的切油 深度、VSV角度瞬时关小量和喷口喉部面积瞬时放大量,并从理论上对试验现象做了解释。结果表明:试验结果与理论分析相一 致,证明试验结果是可靠的;试验结果能够为消喘系统的设计提供参考,在设计消喘系统时,消喘措施的具体调整量需通过试验手 段确定;适当增大切油深度、增加喷口喉部面积瞬时放大量、增加VSV角度瞬时关小量,有利于发动机消喘;加快VSV和喷口等几 何可调特征部件的响应速度,有利于发动机快速退出喘振。
英文摘要:
      In order to determine the impact of surge suppression actions such as combustor short-duration throttle-down,closing com? pressor variable stator vane(VSV)and enlarging nozzle throat area,a test plan was developed for a variable geometry mixed exhaust turbo? fan engine,and a dedicated surge suppression actions verification test was carried out. The fuel cutoff depth,instantaneous amount of VSV closing and instantaneous nozzle throat area increment were obtained when surge suppression failed and succeeded,respectively,the test phenomenon was theoretically explained. The test results are consistent with the theoretical analysis,which proves that the test results are reliable. The test results can provide reference for the design of a surge suppression system,however,the specific adjustment amount of the surge suppression actions should be determined experimentally. Proper increase of fuel cutoff depth,instantaneous nozzle throat area in? crement and instantaneous amount of VSV closing are beneficial to surge suppression. Faster actuation of variable geometry such as VSV and nozzle is helpful for the engine to rapidly recover from the surge.
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