组合发动机可调进气道气动性能

严红明; 钟兢军; 杨凌; 韩吉昂

组合发动机可调进气道气动性能

1.
哈尔滨工业大学能源科学与工程学院,哈尔滨 150001
2.
大连海事大学轮机工程学院,大连 116026

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出版历程
- 收稿日期: 2009-12-28
- 修回日期: 2010-06-22
- 刊出日期: 2011-02-28

Aerodynamic characteristics research on variable geometry inlet of combined cycle engine

1.
School of Energy Science and Engineering, Harbin institute of Technology,Harbin 150001,China
2.
Marine Engineering College, Dalian Maritime University,Dalian 116026,China

摘要

摘要: 为使涡轮/冲压组合发动机能在宽广的飞行高度、速度内飞行,设计一种组合发动机可调进气道气动结构.编制带黏性修正激波系结构预估程序,实现不同来流马赫数及来流攻角下,进气道内激波系结构布置及强度预估,并指导进气道可调楔板尺寸选取.考虑进气道附面层抽吸后,对来流在马赫数为1.6~4.0范围内,-2°,0°和+2°三种攻角下进气道二维流场进行数值计算,流场结构与二维带黏性修正激波系结构预估程序计算结果非常吻合,得到进气道在各工况条件下气动性能,分析了来流马赫数及攻角对调节规律及进气道性能特性的影响规律.
- 涡轮/冲压组合发动机 /
- 可调进气道 /
- 激波系结构 /
- 气动特性 /
- 变工况
Abstract: To enable the flight of turbo/ramjet combined cycle engine within extensive altitude and speed,the aerodynamic structure of a variable geometry inlet for combined cycle engine was designed in this paper.Estimation program of shock structure with viscous correction was compiled to estimate the shock structures and intensities in the inlet under different Mach numbers and attack angles.The choice of the variable panel length was governed by the program.Considering the boundary layer suction,two-dimensional flow fields of the inlet were simulated from Mach number 1.6 to 4.0 at attack angles of -2°,0°,+2°.The structures of the flow fields were consistent with the computed results by the compiled program.Aerodynamic characteristics of the variable geometry inlet were acquired.The influences of Mach numbers and attack angles on the adjustment rules and aerodynamic characteristics of the inlet were analyzed.
- turbo/ramjet combined cycle engine /
- variable geometry inlet /
- shock structures /
- aerodynamic characteristics /
- off-design

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参考文献(13)

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