涡轮空气马达单独螺旋桨试验系统设计与分析  

Design and Analysis of a Separate Propeller Test System for Turbo AirMotors

作　　者：曲明[1] 徐传宝 闫永昌[1] 张连河[1] 刘景飞[1] 李盛文[1] Qu Ming;Xu Chuanbao;Yan Yongchang;Zhang Lianhe;Liu Jingfei;Li Shengwen(Key Laboratory of Aeronautical Science and Technology with Low speedand High Reynolds Number,AVIC Aerodynamics Research Institute,Harbin 150001,China)

机构地区：[1]中国航空工业空气动力研究院低速高雷诺数航空科技重点实验室,黑龙江哈尔滨150001

出　　处：《气动研究与试验》2024年第3期45-51,共7页Aerodynamic Research & Experiment

摘　　要：为在FL-10风洞准确获得螺旋桨缩比模型拉力系数与试验风速、螺旋桨转速、桨叶角及螺旋桨效率的对应关系,本文简要介绍了涡轮空气马达驱动的单独螺旋桨试验系统,设计了高精度流量控制装置、螺旋桨驱动及传动机构、螺旋桨、旋转轴天平,在FL-9风洞进行了测试,测试结果表明,FL-10风洞的涡轮空气马达单独螺旋桨试验系统的核心结构设计合理,运行可靠,有效拓展了FL-10风洞在该领域的试验能力。In order to accurately obtain the relationship between the tension coefficient of the propeller scaled model and the experimental wind speed,propeller speed,blade angle,and propeller efficiency in the FL-1o wind tunnel,this paper developed a separate propeller test system driven by a turboair motor.A high-precision flow control device,propeller drive and transmission mechanism,propeller,and rotating shaft balance were designed and tested in the FL-9 wind tunnel.The test results indicate that the core structure design of the turbine air motor separate propeller test system in the FL-10 wind tunnel is reasonable,operates reliably,and effectively expands the testing capabilities of the FL-10 wind tunnel in this field.

关 键 词：螺旋桨 滑流 风洞试验 动力模拟 

分 类 号：V211.72[航空宇航科学与技术—航空宇航推进理论与工程]