四川兵工学报
四川兵工學報
사천병공학보
SICHUAN ORDNANCE JOURNAL
2014年
7期
60-63
,共4页
高负荷过渡段%扩张规律%落差比%总压恢复系数%优化设计
高負荷過渡段%擴張規律%落差比%總壓恢複繫數%優化設計
고부하과도단%확장규률%락차비%총압회복계수%우화설계
high load transition section%expanding regulation%the ratio of the fall%total pressure recovery coefficient%optimal design
对于具有内外双涵道某型涡扇发动机，其过渡段通道的损失主要来源于沿程损失和附面层分离损失，而影响附面层分离的主要是过渡段通道的扩张规律，落差越大，过渡段的负荷则越高。针对该问题，采用均匀设计的方法设计试验方案，通过CFD数值计算模拟方法对涡扇发动机风扇与压气机之间的过渡段流道进行了气动性能计算。该方法与结果为此类过渡段流道的设计优化提供了参考，并为以后的进一步改进和优化打下了坚实的基础。
對于具有內外雙涵道某型渦扇髮動機，其過渡段通道的損失主要來源于沿程損失和附麵層分離損失，而影響附麵層分離的主要是過渡段通道的擴張規律，落差越大，過渡段的負荷則越高。針對該問題，採用均勻設計的方法設計試驗方案，通過CFD數值計算模擬方法對渦扇髮動機風扇與壓氣機之間的過渡段流道進行瞭氣動性能計算。該方法與結果為此類過渡段流道的設計優化提供瞭參攷，併為以後的進一步改進和優化打下瞭堅實的基礎。
대우구유내외쌍함도모형와선발동궤，기과도단통도적손실주요래원우연정손실화부면층분리손실，이영향부면층분리적주요시과도단통도적확장규률，락차월대，과도단적부하칙월고。침대해문제，채용균균설계적방법설계시험방안，통과CFD수치계산모의방법대와선발동궤풍선여압기궤지간적과도단류도진행료기동성능계산。해방법여결과위차류과도단류도적설계우화제공료삼고，병위이후적진일보개진화우화타하료견실적기출。
For a turbofan engine with double culvert,the transition section channel loss mainly comes from the path loss and the loss of boundary layer separation,the influence of the boundary layer separation is mainly the expansion regulation of the transition section channel regulation,the greater the fall,the load of the transition section is higher.Using uniform design method to design test plan,aerodynamic performance calculation is carried out for the transition section which is between the extractor fan and compressor ma-chine of a turbofan engine by adopting the method of CFD numerical simulation.The methods and results provide a reference for the design and optimization of the transition section and lay a solid foundation for further improvement and optimization for the future.
