摘要
基于气动耦合原理,发展了涡扇发动机风扇出口分流环计算模型,并进一步基于多级轴流压气机系统的逐级单元控制体模型,建立了混合加力涡扇发动机喘振及其喘振消除的数值模拟方法,并将其应用于某型全台加力涡扇发动机过失速特性模拟。在加力状态下采用收小尾喷管喉道面积诱导了风扇压气机过失速—喘振过程,并给出了预先对加力燃烧室实施切油消除风扇压气机喘振数值模拟结果。
A numerical computer model with post-stall analysis capability was established to simulate an augmented turbofan engine. The model was based on stage-by-stage compression control volumes. A technique based on steady flow and a pseudo-flow area was developed to simulate the splitter flow at fan exit. Numerical method was established using MacCormack＇s explicit difference scheme and characteristic boundary treatment. Reducing nozzle throat area was used to induce post-instability operation and the sequences of events leading to surge were investigated. Afterburner-fuel cutdown transient simulation was established to investigate the elimination of surge. The typical behavior and performance of the turbofan engine during surge cycle and the process of surge elimination were obtained.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2006年第2期275-279,共5页
Journal of Aerospace Power
基金
航空科学基金资助(02C53022)
关键词
航空
航天推进系统
涡扇发动机
过失速
喘振
数值模拟
aerospace propulsion system
turbofan engine
post-stall
surge
numerical simulation
