Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense. Washington Headquarters Services, Directorate for Information . 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)2. REPORT TYPE Technical Papers SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) Air Force Research Laboratory (AFMC) AFRL/PRS 5 Pollux Drive Edwards AFB CA 93524-7048 SPONSOR/MONITOR'S ACRONYM(S) SPONSOR/MONITOR'S NUMBER(S) DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution unlimited. DISCUSSIONAs stated above, an advanced expander engine model, which met the IHPRPT Phase I system level goals was established, from which component goals could be determined. Since Pratt & Whitney has extensive history with the RL10A-3-3A, e which is also thebaseline^forjtha-JHPBPT-goals, it was used as our starting point for developing the advanced expander engine cycle. The RL10A-3-3A has 16,500 pound (7484 kg) vacuum thrust, specific impulse of 442.5 seconds, and a thrust to weight ratio of 53. It utilizes a two stage turbine driven by the expanded hydrogen from the combustor and nozzle cooling tubes. The RL10 turbine drives both the two stage hydrogen turbopump and, through a gearbox, the single stage Liquid Oxygen (LOX) turbopump. The maximum cycle pressure is approximately 1100 psia (77.33 kg/cm 2 ) with a chamber pressure of 470 psia (33 kg/cm 2 ). The expander cycle developed for the RL10 is used in each member of the RL10 family, covering the 16,500 to 24,750 pound (7484 -11226 kg) thrust range.The advanced expander engine cycle, established to support the IHPRPT Phase I goals, will _, allow further growth to 50,000 -80,000 pounds (Tntnrt vn±^ I-Qü-C^MMT-design and F«46ii^> _ (22,679 -36,287
The world's first liquid oxygen-liquid hydrogen closed expander cycle engine, the RL10, was created over 44 years ago by Pratt & Whitney Rocketdyne and has been a successful mainstay for the upper stages of US launch vehicles ever since. Continuous improvements over the years have increased the thrust of this engine to over 140%. Recent component development activity includes the cooperative design, manufacture, and test of a single shaft turbopump to replace the geared RL10 turbopumps. In combination with a liquid oxygen boost pump and a combustion chamber being developed by PWR, the single shaft turbopump can increase the RL10 thrust to 35,000 pounds while maintaining reliability, fail-safe operation, and ease of multiple restarts of the expander cycle design. The requirements for the single shaft turbopump are based on Pratt & Whitney Rocketdyne system expertise and US engine development experience, while the actual pump design and its features were based on KBKhA's more than 60 years experience in designing single shaft turbopump. This paper will review various turbopump development approaches and potential opportunities to support engines in the RL10 thrust class. The advantages of both the current geared and the single shaft turbopump configurations will be discussed. This paper will review various configurations for the single shaft turbopump including the alternate positioning of the turbine and pumps as well as various configurations for individual turbine and pump elements. The single shaft turbopump was designed for multiple thrust levels. The development methodology for a pump capable of operating at multiple thrust levels will be discussed. Some of the conceptual designs which were evaluated will be reviewed. KBKhAs approach to developing turbomachinery also addresses rotordynamics methodologies, assembly, maintainability, and off nominal operating conditions. KBKhA's integrated element, subcomponent, component, and turbopump assembly development approach will be discussed. This integrated approach continues through assembly and test of the integrated single shaft turbopump assembly using liquid hydrogen and liquid oxygen. Representative results from tests at each level will be reviewed as well as the plans for testing in the US. The test results will be reviewed to provide an understanding of KBKhA's component development approach. Finally, the potential application of the single shaft turbopumps to increase the thrust of RL10 engines at various thrust levels will be reviewed.
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