某直径11厘米微型扩压器的改型设计(英文)

作     者：陈杰 黄国平 

作者机构：南京航空航天大学微型发动机研究所 

基　　金：KF07001 National Natural Science Foundation of China, NSFC: 30700057 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2010年第23卷第3期

页      码：298-305页

摘      要：In order to improve the performances of an 11 cm-diameter turbine engine,this article suggests to substitute a new-style micro diffuser redesigned based on a new concept for the traditional diffuser having poor performances. The new diffuser comprises integral blades and splitters,which are taken for a series of ducts in designing. This article investigates the effects of the cross-section area distribution along the flow path on the redesigned diffuser＇s performances. Having furnished with the new diffuser in place of the original vaned one,the 11 cm-diameter prototype engine is tested on the rig for its performances. CFD and experiments have shown that the improved diffuser with the unchanged original size has gained excellent performance parameters of pressure coefficient over 0.65 and total pressure recovery coefficient over 0.9. Equipped with the redesigned micro diffuser,the engine increases the thrust by 11% and decreases the specific fuel consumption by 9%.

主 题 词：aerospace propulsion new-style micro diffuser numerical analysis micro turbine engine centrifugal compressor 

学科分类：080704[080704] 08[工学] 0807[工学-电子信息类] 0802[工学-机械学] 0825[工学-环境科学与工程类] 0801[工学-力学类] 

核心收录：

D　O　I：10.1016/S1000-9361(09)60219-3

馆 藏 号：203533607...