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 Design and Test Results of an Advanced Liquid Hydrogen Turbopump written by and published by . This book was released on 1999 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper discusses the design, the test facility, and the test results of an Advanced Liquid Hydrogen Turbopump for a 30,000 pound (22,679 kg) thrust Upper Stage Expander Cycle Engine being developed by Pratt & Whitney Liquid Space Propulsion under contract for the United States Air Force Research Laboratory (AFRL) to support the Integrated High Payoff Rocket Technology (IHPRPT) program. The Advanced Liquid Hydrogen Turbopump is designed to provide improved system thrust to weight, decreased hardware/support costs, and increased reliability. These benefits will be accomplished and demonstrated through design, development, and test of this high speed, high efficiency, two stage hydrogen turbopump capable of supplying 16 lb m/sec (7.3 kg/sec.) of liquid hydrogen at 4600 psia (323.4 kg/sq cm).

Download or read book Liquid Hydrogen Turbopump ALS Advanced Development Program Volume 1 written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-10-29 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: The interface criteria for the Turbopump Test article (TPA) and the Component Test Facility located at NASA, Stennis Space Center is defined by this interface Control Document (ICD). TPA ICD Volume 2 is submitted for the Cold Gas Drive Turbopump Test Article, which is generally similar but incorporates certain changes, particularly in fluid requirements and in instrumentation needs. For the purposes of this ICD, the test article consists of the Hot Fire Drive Turbopump mounted on its test cart, readied for installation in the component test facility. It should be emphasized that the LH2 turbopump program is still in its early concept design phase. Design of the turbopump, test cart, and spools are subject to revisions until successful conclusion of the Detail Design Review (DDR). Lindley, Bruce Unspecified Center...

Download or read book Design and Development of an Advanced Liquid Hydrogen Turbopump written by and published by . This book was released on 1998 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper discusses design and development of an Advanced Liquid Hydrogen Turbopump for a 50,000 pound (22,6?9 kg) thrust Upper Stage Expander Cycle Engine being developed by Pratt & Whitney Liquid Space Propulsion under contract for the United States Air Force Research Laboratory (AFRL) to support the Integrated High Payoff Rocket Technology (IHPRPT) program. The Advanced Liquid Hydrogen Turbopump is designed to provide improved system thrust to weight, decreased hardware/support costs, and increased reliability. These benefits will be accomplished and demonstrated through design, development, and test of this high speed, high efficiency, two stage hydrogen turbopump capable of supplying 16 lbm/sec (7.3 kg/sec.) of liquid hydrogen at 4600 psia (323.4 kg/sq cm).

Download or read book Design and Test of a Radial In flow Turbine for an Advanced Liquid Hydrogen Turbopump written by J. L. Rodriguez and published by . This book was released on 2000 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Design and Test of a Radial Inflow Turbine for an Advance Liquid Hydrogen Turbopump written by and published by . This book was released on 2000 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pratt & Whitney has developed a high performance Radial Inflow Turbine (RIT) to power the Advanced Liquid Hydrogen Turbopump (ALH) for the Upper Stage Demonstrator engine. The design is based on Pratt & Whitney developed RIT methodology that reduces axial length and tip diameter compared to state-of-the-art RIT's, while maintaining or exceeding existing performance levels. The full power speed is very high delivering ruined power to the pump. Included are the design characteristics and preliminary test results at low speed.

Download or read book Experimental Study of Low speed Operating Characteristics of a Liquid Hydrogen Centrifugal Turbopump written by and published by . This book was released on 1969 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Test Results of the Rs 44 Integrated Component Evaluator Liquid Oxygen Hydrogen Rocket Engine written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-04 with total page 402 pages. Available in PDF, EPUB and Kindle. Book excerpt: An advanced LOX/LH2 expander cycle rocket engine, producing 15,000 lbf thrust for Orbital Transfer Vehicle missions, was tested to determine ignition, transition, and main stage characteristics. Detail design and fabrication of the pump fed RS44 integrated component evaluator (ICE) was accomplished using company discretionary resources and was tested under this contracted effort. Successful demonstrations were completed to about the 50 percent fuel turbopump power level (87,000 RPM), but during this last test, a high pressure fuel turbopump (HPFTP) bearing failed curtailing the test program. No other hardware were affected by the HPFTP premature shutdown. The ICE operations matched well with the predicted start transient simulations. The tests demonstrated the feasibility of a high performance advanced expander cycle engine. All engine components operated nominally, except for the HPFTP, during the engine hot-fire tests. A failure investigation was completed using company discretionary resources. Sutton, R. F. and Lariviere, B. W. Unspecified Center AD-A277085, NASA-CR-194443, NAS 1.26:194443, RI/RD92-127, E-8305 NAS3-23773...

Download or read book Advanced Earth to orbit Propulsion Technology 1994 written by Robert J. Richmond and published by . This book was released on 1994 with total page 690 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Concept Design of a Split Flow Liquid Hydrogen Turbopump written by Michael A. Arguello and published by . This book was released on 2008 with total page 206 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Upper Stage Demonstrator written by and published by . This book was released on 2004 with total page 226 pages. Available in PDF, EPUB and Kindle. Book excerpt: The 50K LOX/LH2 Upper Stage Demonstrator (USD) rocket engine program was designed to meet IHPRPT Phase I goals. The engine design met these goals through the application of three new technology areas for upper stage rocket engines. One was the Advanced Liquid Hydrogen (ALH) turbopump with hydrostatic bearings supports. The second was the Advanced Expander Combustor (AEC) copper-tubular combustion chamber. The third was a digital electronic engine controller that would enable precision control and increased reliability. The culmination of this program was to be demonstration testing of an engine comprised of these advanced components. However, problems arose during the ALH and AEC component programs that prevented these two components from being engine test ready. The technology advancements, shortfalls, lessons learned, and future recommendations from these programs have identified improvement areas in analysis tools/modeling for the next generation of rocket engines. The system level architecture and plans developed for the USD can be modified and used on a future program that incorporates new technology components at the engine level.

Download or read book Advanced Liquid Oxygen LO2 Propellant Conditioning Concept Testing written by and published by . This book was released on 1995 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Research and Technology Program Digest written by United States. National Aeronautics and Space Administration and published by . This book was released on with total page 792 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Reports and Documents written by United States. Congress and published by . This book was released on with total page 1860 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Authorizing Appropriations to the National Aeronautics and Space Administration written by United States. Congress. House. Committee on Science and Astronautics and published by . This book was released on 1962 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book History of Liquid Propellant Rocket Engines written by George Paul Sutton and published by AIAA. This book was released on 2006 with total page 936 pages. Available in PDF, EPUB and Kindle. Book excerpt: Liquid propellant rocket engines have propelled all the manned space flights, all the space vehicles flying to the planets or deep space, virtually all satellites, and the majority of medium range or intercontinental range ballistic missiles.