核心机派生涡扇发动机部件及整机匹配

欧阳辉; 朱之丽; 俞伯良

核心机派生涡扇发动机部件及整机匹配

1.
北京航空航天大学能源与动力工程学院,北京 100191
2.
中国航空工业集团公司中国燃气涡轮研究院,成都 610500

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- 被引次数: 0
出版历程
- 收稿日期: 2009-08-03
- 修回日期: 2009-12-01
- 刊出日期: 2010-09-28

Components and engine matching of core-derived turbofan

1.
1. School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing 100191,China
2. China Gas Turbine Establishment,Aviation Industry Corporation of China,Chengdu 610500,China
2.
1. School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing 100191,China
2. China Gas Turbine Establishment,Aviation Industry Corporation of China,Chengdu 610500,China

摘要

摘要: 以核心机与低压系统的部件及整机气动热力匹配关系为理论依据,在全面考虑低压压缩系统与核心机压气机的匹配约束关系、核心机涡轮工作状态相应变化以及派生发动机内外涵整机匹配的多因素下,建立了核心机派生涡扇发动机部件及整机气动热力循环匹配算法模型.应用该模型,进行了核心机派生涡扇发动机循环参数及性能趋势分析,计算结果表明高低压和整机匹配约束直接影响核心机派生涡扇发动机循环参数和整机性能,为核心机派生系列化涡扇发动机工程实践应用中所涉及的部件/整机参数匹配及性能预估提供分析和设计参考.
- 核心机 /
- 涡扇发动机 /
- 低压系统 /
- 发动机匹配 /
- 派生
Abstract: The gas turbine core-engine derivative model for turbofan serialization,which focused on thermo-cycle approach,was established based on components and engine matching between core-engine and low-pressure system.The model took into account high-low system interaction,core turbine operation and inner-outer duct compatibility comprehensively,and then it was utilized to analyze derived turbofans' cycle and performance.The results show that the coupled low-high systems' constraints influence turbofan's performance and cycle parameters,providing engineering reference and design criteria for core-derived turbofan's matching and simulation.
- core-engine /
- turbofan /
- low-pressure system /
- engine matching /
- derivative