摘要
为定量获得某发动机在温度畸变条件下的特性,采用有效的畸变传递模型,就进气温度畸变对某发动机稳定性和性能的影响进行了较深入的数值研究。详细地计算了温度畸变对发动机稳定性和性能的影响结果,讨论了温度畸变作用下该发动机的多种重要特性。结果表明,所研究的三组温升率均超过了临界温升率,临界高温区范围为180°;温度敏感系数均在统计范围之内,表明该发动机具有较好的抗温度畸变能力。而在上限温度畸变作用下,发动机必须使用防喘系统。
In order to abtain the performance of an acro-engine under the condition of temperature distortion, this paper presents the numerical investigation of the effect of the inlet temperature distortion upon the stability and performance of aeroengine using the effective distortion-transfer model. The calculation results indicate that three group of temperature increase rates investigated exceeded the critical value. The critical range of the high temperature section is about 180° circumferential. The engine sensibility coefficients to temperature distortion are within the statistical range, which shows that engine has the ability of antitemperature distortion. The anti-surge system must used when there is excessive temperature distortion.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2008年第6期677-680,共4页
Journal of Propulsion Technology
基金
航空基础科学基金资助项目(03124001)
关键词
温度畸变
温升率
稳定裕度损失
Temperature distortion
Temperature increase rate
Stability margin degradation
作者简介
叶巍（1968～），男，高级工程师，博士生，研究领域为航空发动机稳定性设计与评定。E-mail：yewei-gte@sina．com
