SBIR Phase II: Design-Based Developments for Pump Cavitation Control

SBIR 第二阶段：基于设计的泵气蚀控制开发

• 批准号: 0078582
• 负责人: Daniel Baun
• 金额: $ 39.99万
• 依托单位: CONCEPTS ETI, INC.
• 依托单位国家: 美国
• 项目类别: Standard Grant
• 财政年份: 2001
• 资助国家: 美国
• 起止时间: 2001-01-01 至 2002-12-31
• 项目状态: 已结题
• 来源: https://www.nsf.gov/awardsearch/showAward?AWD_ID=0078582&HistoricalAwards=false
• 关键词: SBIR; Phase; II; Design; Based

This Small Business Innovation Research Phase II project is to provide the means to reliably calculate turbopump stiffness and damping matrices based on dynamic force measurements collected using a magnetic bearing rig. During Phase I exploratory development of a high suction specific speed (NSS) = 65,000 rocket engine turbopump pump stage was carried out and laid the foundation for this project. A complementary Phase I project for NASA focused on an NSS = 85,000 stage. Earlier Air Force funding concentrated on demonstrating magnetic bearings as a useful lab instrument. More recent breakthroughs include a novel fix for auto-oscillation and establishing the structure of an innovative dynamic force matrix measurement methodology. The primary challenge in this work is to isolate those forces on the rotor (with and without cavitation) due to the interaction of the impeller with the stator using innovative test and signal processing techniques. By testing a series of impellers, a database of rotordynamic coefficients will be established based on component dynamic force data. An additional objective is to evaluate the capability of CFD for replicating those physical force measurements. The goal is to create scientifically based design methods for lighter high-performance turbopumps. Smaller, lighter, and higher speed rocket engine turbopumps are required to meet lower space launch cost requirements. Successful accomplishment of this fundamentally based approach for measuring component specific rotor dynamic forces and a method for using experimental results on a broader basis in the design process can lead to a breakthrough technology. It will enable turbopump designers to overcome current thresholds due to hydraulic induced rotor dynamic instabilities. In addition to reducing equipment size and cost, reliability will improve. The technology is also applicable to industrial turbomachinery including industrial pumps, aircraft engine fuel pumps, and compressors.

这个小型企业创新研究的第二阶段项目是提供一种可靠的方法来计算涡轮泵的刚度和阻尼矩阵，该方法基于使用磁轴承平台收集的动态力测量。一期进行了高吸比转速(NSS) = 65000火箭发动机涡轮泵泵级的探索性开发，为本项目奠定了基础。NASA的补充第一阶段项目侧重于NSS = 85,000阶段。早期的空军资金集中在证明磁轴承是一种有用的实验室仪器。最近的突破包括一种新的自振荡修复和建立一种创新的动态力矩阵测量方法的结构。这项工作的主要挑战是利用创新的测试和信号处理技术来隔离由于叶轮与定子相互作用而产生的转子上的力（有或没有空化）。通过对一系列叶轮进行试验，建立基于部件动力数据的转子动力系数数据库。另一个目标是评估CFD复制这些物理力测量的能力。目标是为更轻的高性能涡轮泵创造科学的设计方法。更小、更轻、更高速度的火箭发动机涡轮泵需要满足更低的空间发射成本要求。成功地完成这种基于测量部件特定转子动力的基本方法，以及在设计过程中更广泛地使用实验结果的方法，可以导致突破性的技术。它将使涡轮泵设计人员能够克服由于水力诱导转子动态不稳定而产生的电流阈值。除了减少设备尺寸和成本外，可靠性也将得到提高。该技术也适用于工业涡轮机械，包括工业泵、飞机发动机燃油泵和压缩机。