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 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 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 Final Report Volume 2 Nitrogen and Ambient Oxygen Testing written by and published by . This book was released on 1990 with total page 159 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report covers the testing of a rocket engine oxygen turbopump (TPA) using high pressure ambient temperature nitrogen and oxygen as the turbine drive gas in separate test series. The pumped fluid was liquid nitrogen or liquid oxygen. The TPA is designed to operate with 400 F oxygen turbine drive gas. Following bearing tests, the TPA was finish machined (impeller blading and inlet/outlet ports). The hydrostatic bearing system requires a bearing pressurization system. Two test series were successfully completed with the bearing assist supplied only by the pump second stage output which entailed a rubbing start until pump pressure builds up. The final test series used ambient oxygen drive and no external bearing assist. Total operating time was 2268 seconds. There were 14 starts without bearing assist and operating speeds up 80, 000 rpm were logged. Teardown examination showed some smearing of silverplated bearing surfaces but no exposure of the underlying monel material. There was no evidence of melting or oxidation due to the oxygen exposure. The articulating, self-centering hydrostatic bearing exhibited no bearing load or stability problems. The only anomaly was higher than predicted flow losses which were attributed to a faulty ring seal. The TPA will be refurbished prior to the 400 F oxygen test series but its condition is acceptable, as is, for continued operating.

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 602 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Download or read book Government Reports Annual Index written by and published by . This book was released on 1993 with total page 1452 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Announcements Index written by and published by . This book was released on 1991 with total page 624 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Monthly Catalogue United States Public Documents written by and published by . This book was released on 1995 with total page 868 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Orbital Transfer Rocket Engine Technology Advanced Engine Study written by and published by . This book was released on 1992 with total page 302 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Orbit Transfer Rocket Engine Technology Program written by Leonard Schoenman 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 Technology for Large Space Systems written by and published by . This book was released on 1987 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Annual Index Keyword A L written by and published by . This book was released on 1984 with total page 1000 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Future Orbital Transfer Vehicle Technology Study Volume 1 Executive Summary written by Eldon E. Davis and published by . This book was released on 1982 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Future Orbital Transfer Vehicle Technology Study Volume 2 Technical Report written by Eldon E. Davis and published by . This book was released on 1982 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study has the objective of identifying missions for future orbit transfer vehicles (1995-2010) and defining the technology, operations and vehicle concepts that satisfy the transportation requirements. Several issues were examined. The first involved comparison of reusable space and ground based LO2/LH2 OTV's. Both vehicles used advanced space engines and aero assist capability. The SB OTV provided advantages in life cycle cost, performance and potential for improvement. The second issue was the comparison of an all LO2/LH2 OTV fleet with a fleet of LO2/LH2 OTVs and electric OTV's. The normal growth technology electric OTV used silicon cells with heavy shielding and argon ion thrusters. In this case, the LO2/LH2 OTV fleet provided a 23% advantage in total transportation cost. The third issue dealt with the impact of accelerated technology. An accelerated technology LF2/LH2 OTV provided improvements in performance relative to LO2/LH2 OTV but had higher DDT & E cost which negated its cost effectiveness. The accelerated technology electric vehicle used GaAs cells and annealing but still did not result in the mixed fleet being any cheaper than an all LO2/LH2 OTV fleet. The study conclusion is that reusable LO2/LH2 OTV's can serve all general purpose cargo roles between LEO and GEO for the foreseeable future. The most significant technology for the second generation vehicle would be space debris protection, on-orbit propellant storage and transfer and on-orbit maintenance capability.

Download or read book Orbit transfer vehicle engine technology program written by P. T. Coleman and published by . This book was released on 1989 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Orbit Transfer Rocket Engine Technology 7 5K LB Thrust Rocket Engine Preliminary Design written by T. J. Harmon and published by . This book was released on 1993 with total page 233 pages. Available in PDF, EPUB and Kindle. Book excerpt: A preliminary design of an advanced LOX/ LH2 expander cycle rocket engine producing 7,500 lbf thrust for Orbital Transfer vehicle missions was completed. Engine system, component and turbomachinery analysis at both on design and off design conditions were completed. The preliminary design analysis results showed engine requirements and performance goals were met. Computer models are described and model outputs are presented. Engine system assembly layouts, component layouts and valve and control system analysis are presented. Major design technologies were identified and remaining issues and concerns were listed. Orbit Transfer Vehicle(OTV). Expander cycle, Hydrogen/oxygen rocket engine, Space based engine. High pressure fuel turbopump.