Advanced Turbopump High Stage Loading, Enhanced Efficiency, and Reduced Part Count
Agency / Branch:
DOD / USAF
Achieving by the year 2010 a significant reduction in part count, cost, size and weight of turbopumps, and improving their reliability and efficiency is accomplished with a series of innovative single stage high head (150,000-200,000 ft) demonstrator pumps which identify critical technological questions, validate design principles and tools, and set the path to realize the IHPRPT Phase II and III goals. Fluid dynamically advanced bowed blading, with non-linear thickness and extended rake, increased taper, and a range of impeller backsweep angles plus advanced materials are used with the intent of improving efficiency by 5-10 points while obtaining a stable operating envelope extending to below 50% of Q/N (equating to roughly a 20:1 thrust ratio, depending on engine type) with sufficient structural integrity to give a good design lift. Phase I defines the path to these objectives. It establishes the framework of several advanced generation single stage pumps which will be tested during Phase II. Alternate diffuser systems are considered. A novel assessment of total pressure losses and static pressure recoveries will be made throughout the pump. The proposed technology is aimed at and beyond the Phase III P&W ARPP for the IHPRPT and will also be transferred to industrial pumps.
Small Business Information at Submission:
Principal Investigator:Robert T. Kendall, Sr.
Concepts Eti, Inc.
4 Billings Farm Road Grants Pass, OR 97527
Number of Employees: