摘要
尾推式微型涡桨发动机主要由螺旋桨产生推力,喷管在产生剩余推力的同时会与螺旋桨产生复杂的气动干扰。为探究在这种气动干扰下尾推式微型涡桨发动机推力特性的变化规律,在计算上验证了MRF(移动参考系)方法在推进式微型涡桨发动机推力特性计算方面的可行性,开展了螺旋桨、喷管和短舱一体化构型的CFD(计算流体动力学)计算,得到了在地面慢车和巡航阶段时不同喷管压比、喷射角、螺旋桨转速和来流马赫数对发动机推力特性的影响规律。经分析发现:在地面状态下,喷射角为0°时,螺旋桨推力系数始终大于0.1,在同样压比下总推力最大可相差36%;喷射角为0°~60°时,螺旋桨推力系数随压比增大而减小;喷射角为90°时随压比的增大而增大。在巡航状态下,喷射角和压比对桨推力系数影响较小,桨推力系数随来流马赫数的增大而减小,随桨转速的增大而增大。两种状态下喷射角为0°时喷管剩余推力最大,获得的总推力最大,表现出良好的推力特性。
The thrust of the propulsive micro turboprop engine was produced primarily by the propeller.Not only did the nozzle generate residual thrust,but also it could make complex aerodynamic interference with the propeller.In order to explore the variation of thrust characteristics of propulsive micro turboprop engines under interference,the feasibility of the MRF(moving reference frame)method in calculating thrust characteristics of propulsive micro turboprop engines was verified.The CFD(computational fluid dynamics)calculation for the integrated configuration of the propeller,nozzle and nacelle was conducted.The influences of different nozzle pressure ratios,injection angles,propeller speeds,and incoming Mach numbers on the thrust characteristics of the engine during the idling and cruise states were obtained.It was found that,in the ground state,when the injection angle was 0°,the thrust coefficient of the propeller was greater than 0.1,and the maximum difference of the total thrust can reach 36%under the same pressure ratio;when the injection angle was 0°—60°,the propeller thrust coefficient decreased with the pressure ratio,but increased at the injection angle of 90°.In the cruise state,the injection angle and pressure ratio had less influence on the thrust coefficient of the propeller.In contrast,the propeller thrust coefficient decreased with the incoming Mach number and increased with the propeller speed.When the injection angle was 0°,the nozzle’s remaining thrust was maximum,and the total thrust was maximum in these two states,showing good thrust characteristics.
作者
黑少华
杨晨
师晨月
杨金广
HEI Shaohua;YANG Chen;SHI Chenyue;YANG Jinguang(School of Energy and Power Engineering,Dalian University of Technology,Dalian Liaoning 116024,China)
出处
《航空动力学报》
北大核心
2025年第9期62-72,共11页
Journal of Aerospace Power
基金
中央高校基本科研业务费专项资金(DUT24RC(3)001)。
关键词
尾推式
微型涡桨发动机
螺旋桨
喷管
推力特性
propulsive
micro turboprop engine
propeller
nozzle
thrust characteristic
