动力模拟风洞试验中标准推阻分解方法的适用性分析  

Analysis of the Limitation of Standard Bookkeeping Method in Turbine Powered Simulation Wind Tunnel Test

作　　者：陈莹[1] 巴玉龙[1] 王奇志[1] 郭传亮 CHEN Ying;BA Yulong;WANG Qizhi;GUO Chuanliang(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《民用飞机设计与研究》2018年第4期24-28,共5页Civil Aircraft Design & Research

摘　　要：从标准推阻分解方法(Standard-Bookkeeping-Method,简称SBM)的原理出发,分析了该方法在不同发动机模拟状态下的适用性。当发动机风扇压比高、喷管流动达到超音速(壅塞)状态时,动力模拟试验采用SBM方法计算质量流量和推力,其结果是正确的;当发动机风扇压比低、喷管流动为亚声速流动状态时,此时质量流量和动力模拟器的推力计算与外涵出口平面处的静压相关,SBM方法中喷口处静压Pe与前方来流静压P0相等的假设,导致计算中引入误差从而影响动力干扰分析。文中给出了不同静压差引起的质量流量和推力误差量,表明在动力模拟风洞试验中应测量外涵出口平面处的静压以获得可靠的动力干扰量。Based on the calculation theory of Standard-Bookkeeping-Method (SBM),the possibility and limitations of SBM using in TPS wind tunnel test was analyzed.For high fan nozzle pressure ratio situation,the flow in the fan nozzle exit plane is always at choked condition.The mass flow ratio and thrust force calculation are independent of the static pressure of the flow at the nozzle exit plane.SBM is suitable for this condition.For lower fan nozzle pressure ratio power setting condition,the flow in the fan nozzle exit plane is subsonic.The mass flow and thrust are a function of the static pressure in the exit plane Pe.And SBM calculated by assuming that Pe is equal to the static pressure of free stream P0.The error introduced by the difference between Pe and P0 could not be neglected for lower fan nozzle pressure ratio situation.The error of the mass flow and thrust caused by static pressure in the exit plane were gave out in this paper.It's strongly recommended to measure the static pressure in the nozzle exit plane for TPS wind tunnel te.st.

关 键 词：涡轮动力模拟器 标准推阻分解方法 风洞试验 冲压阻力 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]