Download or read book Design and Test of an Oxygen Turbopump for a Dual Expander Cycle Rocket Engine written by P. S. Buckmann and published by . This book was released on 1989 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Design of an Oxygen Turbopump for a Dual Expander Cycle Rocket Engine written by William S. Strain and published by . This book was released on 2008 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1994 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of the Performance Potential of a Liquid Oxygen Expander Cycle Rocket Engine written by Dylan Thomas Stapp and published by . This book was released on 2016 with total page 163 pages. Available in PDF, EPUB and Kindle. Book excerpt: This research effort sought to examine the performance potential of a dual-expander cycle liquid oxygen-hydrogen engine with a conventional bell nozzle geometry. The analysis was performed using the NASA Numerical Propulsion System Simulation (NPSS) software to develop a full steady-state model of the engine concept. Validation for the theoretical engine model was completed using the same methodology to build a steady-state model of an RL10A-3-3A single expander cycle rocket engine with corroborating data from a similar modeling project performed at the NASA Glenn Research Center. Previous research performed at NASA and the Air Force Institute of Technology (AFIT) has identified the potential of dual-expander cycle technology to specifically improve the efficiency and capability of upper-stage liquid rocket engines. Dual-expander cycles also eliminate critical failure modes and design limitations present for single-expander cycle engines. This research seeks to identify potential LOX Expander Cycle (LEC) engine designs that exceed the performance of the current state of the art RL10B-2 engine flown on Centaur upper-stages. Results of this research found that the LEC engine concept achieved a 21.2% increase in engine thrust with a decrease in engine length and diameter of 52.0% and 15.8% respectively compared to the RL10B-2 engine. A 5.89% increase in vacuum specific impulse was also observed. The implications of these results could lead to significant launch cost savings and replacement of aging expander cycle technology in the rocket propulsion industry. In order to fully validate the results of this research, more knowledge is required regarding the heat transfer characteristics of supercritical oxygen for rocket thrust chamber cooling. Future work in this topic will focus on experimental LOX heat transfer research and model optimization to improve heat transfer estimations in the baseline model developed in this research and further explore the optimal performance potential and limitations of the LEC engine.
Download or read book Design of an Oxygen Turbopump for Use in an Advanced Expander Test Bed Engine written by William W. Pattison and published by . This book was released on 1993 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Orbital Transfer Vehicle Oxygen Turbopump Technology Volume 3 Hot Oxygen Testing written by and published by . This book was released on 1992 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Papers Presented at the AIAA ASME SAE ASEE 25th Joint Propulsion Conference written by and published by . This book was released on 1989 with total page 432 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Annual Report written by Lewis Research Center and published by . This book was released on with total page 264 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Annual Report 1989 written by Lewis Research Center and published by . This book was released on 1989 with total page 256 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Turbopump Systems for Liquid Rocket Engines written by and published by . This book was released on 1974 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Advanced Earth to orbit Propulsion Technology 1994 written by R. J. Richmond and published by . This book was released on 1994 with total page 644 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Orbital Transfer Vehicle Oxygen Turbopump Technology Final Report Volume 1 Design Fabrication and Hydrostatic Bearing Testing written by and published by . This book was released on 1990 with total page 251 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report covers design, fabrication, and initial testing of a rocket engine turbopump (TPA) for delivery of high - pressure liquid oxygen using hot oxygen for the turbine drive fluid. This TPA is basic to the dual expander engine which uses both oxygen and hydrogen as working fluids. All material selections emphasized compatibility with hot oxygen. The OX TPA design uses a two-stage centrifugal pump driven by a single-stage axial turbine on a common shaft. The first pump stage incorporates an inducer section for improved suction performance. Inter-stage pump flow is routed external to the main housing through two ducts connecting first-stage discharge to second stage entry. The shaft is supported by two journal type hydrostatic bearing supplied with high pressure LOX from the second-stage pump discharge. The design includes ports for three shaft displacement/speed sensors, various temperature measurements, and accelerometers. The unique spherical hydrostatic bearing design was considered a radical enough departure from current design to warrant a bearing test program. Series A testing demonstrated bearing chilldown and integrity at low speed operation. An incompletely resolved problem was the rotor binding caused by pressure changes as the tester was chilled to liquid nitrogen temperatures. Series B testing demonstrated the bearing operation at high speed with maximum speed of 72 000 rpm. The bearing operated satisfactorily with no load or stability problems. Post test examination of the journal and thrust bearing surfaces showed no evidence of operating wear.
Download or read book Orbital Transfer Vehicle Oxygen Turbopump Technology Volume 3 written by National Aeronaut Administration (Nasa) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-10 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report covers the work done in preparation for a liquid oxygen rocket engine turbopump test utilizing high pressure hot oxygen gas for the turbine drive. The turbopump (TPA) is designed to operate with 400 F oxygen turbine drive gas. The goal of this test program was to demonstrate the successful operation of the TPA under simulated engine conditions including the hot oxygen turbine drive. This testing follows a highly successful series of tests pumping liquid oxygen with gaseous nitrogen as the turbine drive gas. That testing included starting of the TPA with no assist to the hydrostatic bearing. The bearing start entailed a rubbing start until the pump generated enough pressure to support the bearing. The articulating, self-centering hydrostatic bearing exhibited no bearing load or stability problems. The TPA was refurbished for the hot gas drive tests and facility work was begun, but unfortunately funding cuts prohibited the actual testing. Urke, Robert L. Unspecified Center...
Download or read book Testing of an Advanced Liquid Hydrogen Turbopump written by and published by . This book was released on 2000 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper discusses the testing of an Advanced Liquid Hydrogen Turbopump for a 50,000 pound (222.4 kN) thrust Upper Stage Expander Cycle Engine being developed by Pratt & Whitney Liquid Space Propulsion under contract to the United States Air Force Research Laboratory (AFRL) to support the Integrated High Payoff Rocket Propulsion Technology (IHPRPT) program. The Advanced Liquid Hydrogen (ALH) Turbopump is designed to provide improved system thrust to weight decreased hardware/support costs, and increased reliability. These benefits will be demonstrated through test of this high speed, high efficiency, two stage hydrogen turbopump.
Download or read book Cold air Performance Evaluation of Scale Model Oxidizer Pump drive Turbine for the M 1 Hydrogen oxygen Rocket Engine written by Richard J. Roelke and published by . This book was released on 1966 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Orbit Transfer Rocket Engine Technology Program Oxygen Materials Compatibility Testing written by and published by . This book was released on 1989 with total page 240 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Liquid Rocket Engine Axial flow Turbopumps written by and published by . This book was released on 1978 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt:
