Experimental performance and acoustic investigation of modern, counterrotating blade concepts
Experimental performance and acoustic investigation of modern, counterrotating blade concepts
复制标题
现代反向旋转叶片概念的实验性能和声学研究
DOI：
--
复制
发表时间：
1990
期刊：
影响因子：
--
通讯作者：
G. Hoff
中科院分区：
文献类型：
--
作者：
G. Hoff
从理论和实验两方面对反向旋转叶片的气动、声学和气动性能进行了评价。分析方法的开发和设计。利用在这项工作中发展起来的分析方法，开发了气动和气动声学预测，并将其与NASA和GE风洞测试结果进行了比较。介绍了五种不同的复合材料壳体/钛梁对旋叶片组结构的详细机械设计与制造。设计理念，分析方法和材料几何，以及空气动力学，空气力学和空气声学对设计过程的影响。详细介绍了叶片制造和质量控制程序；介绍了叶片完整性台架试验的步骤和结果；并确定了与台架测试相关的仪器。描述了支持专门测试的其他硬件，以及操作刀片仪器和相关的应力限制。这五个反向旋转叶片的概念被缩放到2英尺的尖端直径，因此它们可以被整合到MPS（模型推进模拟器）中。气动和气动声学性能测试在NASA刘易斯8 × 6超音速和9 × 15 V/STOL（垂直或短距起降）风洞和GE自由射流消声测试室（Cell 41）中进行，以生成这些反旋转叶片设计的实验数据库。提供了测试设备和MPS车辆矩阵，并介绍了测试程序。讨论了对旋翼间距、迎角、塔架距离、叶片数、尾叶直径减小和转子转速不匹配等性能的影响。并给出了对旋叶片和专业气动轮毂稳定性试验结果。
The aerodynamic, acoustic, and aeromechanical performance of counterrotating blade concepts were evaluated both theoretically and experimentally. Analytical methods development and design are addressed. Utilizing the analytical methods which evolved during the conduct of this work, aerodynamic and aeroacoustic predictions were developed, which were compared to NASA and GE wind tunnel test results. The detailed mechanical design and fabrication of five different composite shell/titanium spar counterrotating blade set configurations are presented. Design philosophy, analyses methods, and material geometry are addressed, as well as the influence of aerodynamics, aeromechanics, and aeroacoustics on the design procedures. Blade fabrication and quality control procedures are detailed; bench testing procedures and results of blade integrity verification are presented; and instrumentation associated with the bench testing also is identified. Additional hardware to support specialized testing is described, as are operating blade instrumentation and the associated stress limits. The five counterrotating blade concepts were scaled to a tip diameter of 2 feet, so they could be incorporated into MPS (model propulsion simulators). Aerodynamic and aeroacoustic performance testing was conducted in the NASA Lewis 8 x 6 supersonic and 9 x 15 V/STOL (vertical or short takeoff and landing) wind tunnels and in the GE freejet anechoic test chamber (Cell 41) to generate an experimental data base for these counterrotating blade designs. Test facility and MPS vehicle matrices are provided, and test procedures are presented. Effects on performance of rotor-to-rotor spacing, angle-of-attack, pylon proximity, blade number, reduced-diameter aft blades, and mismatched rotor speeds are addressed. Counterrotating blade and specialized aeromechanical hub stability test results are also furnished.