Development of High-Bypass Ratio Turbofan Aeroengine

doi:10.16080/j.issn1671-833x.2008.13.006

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Development of High-Bypass Ratio Turbofan Aeroengine

更新时间：2025-10-30

- Development of High-Bypass Ratio Turbofan Aeroengine
- Aeronautical Manufacturing Technology Vol. 51, Issue 13, Pages: 40-45(2008)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院
- 作者简介：
- 基金信息：
- DOI：10.16080/j.issn1671-833x.2008.13.006
  CLC：
- Published：2008
- 稿件说明：
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陈光. 高涵道比涡轮风扇发动机发展综述[J]. 航空制造技术, 2008, 51(13): 40-45.

Development of High-Bypass Ratio Turbofan Aeroengine[J]. Aeronautical Manufacturing Technology, 2008, 51(13): 40-45.
陈光. 高涵道比涡轮风扇发动机发展综述[J]. 航空制造技术, 2008, 51(13): 40-45. DOI： 10.16080/j.issn1671-833x.2008.13.006.

Development of High-Bypass Ratio Turbofan Aeroengine[J]. Aeronautical Manufacturing Technology, 2008, 51(13): 40-45. DOI： 10.16080/j.issn1671-833x.2008.13.006.

摘要

作为干线客机的动力，高涵道比涡扇发动机从诞生时起，就在满足飞机需要的前提下，不断完善性能，包括提高推力，降低发动机耗油率与性能衰减率，提高发动机可靠性与耐久性，降低发动机噪声值与排放值等。特别是进入21 世纪后，为用户提供经济性好、能满足新世纪严格环保要求的发动机，已成为参与新型旅客机发动机市场竞争的必备条件。

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Development of High-Bypass Ratio Turbofan Aeroengine

DOI：10.16080/j.issn1671-833x.2008.13.006

摘要

Abstract

关键词

Keywords

references