Study of design method for the zero-stage compressor in an expendable gas turbine engine

LIU Ke-hui; SHAN Peng; LI Na; ZHENG Yan

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Study of design method for the zero-stage compressor in an expendable gas turbine engine

更新时间：2026-07-07

- Study of design method for the zero-stage compressor in an expendable gas turbine engine
- Vol. 21, Issue 6, (2006)
- 作者机构：
  
  1. 中国航天科工集团31所,北京,100074
  2. 北京航空航天大学能源与动力工程学院,北京,100083
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2006
- 稿件说明：
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LIU Ke-hui, SHAN Peng, LI Na, et al. Study of design method for the zero-stage compressor in an expendable gas turbine engine[J]. 2006, 21(6).
DOI：

LIU Ke-hui, SHAN Peng, LI Na, et al. Study of design method for the zero-stage compressor in an expendable gas turbine engine[J]. 2006, 21(6). DOI：

摘要

对法国MicroTurbo公司TRI60系列中基本型TRI60-2向TRI60-20型演变过程进行了分析

研究加零级压气机的技术特点和设计方法。本文以获得TRI60-20压气机部件及特性为主线

阐述了加零级的设计流程

并利用经过试验数据验证的CFD软件对所设计的压气机流场进行了全三维数值模拟和计算分析。结果表明

本文采取的加零级方法是成功的。

Abstract

Analyzing the evolvement from TRI60-2 engine to TRI60-20 engine developed by France MicroTurbo Inc

the technical characteristic and design method of adding zero-stage compressor were researched.Taking obtaining the compressor’s structure and characteristics as the primary concern

the process of adding zero-stage compressor was discussed

and using CFD software validated by test data the flow field was numerically simulated in full three dimensions and analyzed through computation.The result indicates that the method of adding zero-stage compressor discussed in this paper is basically successful.

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Related Institution

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