摘要
以成熟的核心机为基础,匹配带不同涵道比风扇(或带增压级)的低压系统,可以派生出不同推力级别的军用或民用涡扇发动机。本文以核心机派生中的部件/整机气动热力匹配关系为理论依据,建立了核心机派生涡扇发动机匹配和性能计算模型,该模型能对核心机在不同工作点下匹配不同低压系统所派生的发动机进行方案设计,并对其设计点和非设计点性能进行预估。
Series of turbofan for both military and civil applications could be derived based on mature gas turbine core-engine by matching compatible fan （or together with booster） low-pressure system with it. The core-derivative model was established in this paper based on thermo-cyele theory of components and engine matching, which could design derived turbofan＇s cycle scheme with different low-pressure system matched to core-engine on selected working-point, and predict the turbofan＇s performance both in design and off-design condition.
出处
《燃气涡轮试验与研究》
2010年第2期10-14,共5页
Gas Turbine Experiment and Research
关键词
核心机
涡扇发动机
派生
匹配
core-engine
turbofan
derivative
matching
