Study of the design method of an improved micro diffuser

CHEN Jie; HUANG Guo-ping; LIANG De-wang

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Study of the design method of an improved micro diffuser

更新时间：2026-07-07

- Study of the design method of an improved micro diffuser
- Vol. 25, Issue 5, (2010)
- 作者机构：
  
  南京航空航天大学能源与动力学院微型发动机研究所,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2010
- 稿件说明：
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CHEN Jie, HUANG Guo-ping, LIANG De-wang. Study of the design method of an improved micro diffuser[J]. 2010, 25(5).
DOI：

CHEN Jie, HUANG Guo-ping, LIANG De-wang. Study of the design method of an improved micro diffuser[J]. 2010, 25(5). DOI：

摘要

在某直径6cm级的微型涡轮发动机MJ-S1研制中微型扩压器方案得到了改进

改进型微型扩压器由完整的主叶片和通道后部的分流叶片构成

可以避免气流的强烈掺混

降低转弯段内气流速度

减小流动损失.介绍了这种扩压器的设计方法

采用数值模拟的方法研究了设计参数通道面积和叶片角分布对扩压器性能的影响.MJ-S1最佳的改进型扩压器具有上凸的通道面积分布和接近线性的叶片角分布

该扩压器在压气机级中工作时总压恢复系数接近0.9.

Abstract

The improved micro diffuser was suggested in the design of a 6cm-diameter micro turbine engine MJ-S1. The improved micro diffuser

which is composed of the full blades and splitters in the passage rear

can avoid significant mixing of airflow and air velocity of annular turning bend while reducing Mach number losses. The design method of the improved diffuser was put forward in this paper. The effects of passage area and blade angle on the diffuser characteristic were studied by using the computation fluid dynamic code NAPA. The diffuser has higher performance when the passage area distribution is convex and the blade angle is nearly linear. The calculation results show that the total pressure recovery coefficient of the improved diffuser can approach 0.9

when it is operated in the centrifugal compressor stage.

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Related Institution

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