The rocketdyne mark 3 turbopump was a real workhorse of the early space race. Bni teamed with rocketdyne to design and build a second turbopump for nasas lcbt program. Ive drawn this in three colors because a turbopump can be thought of as having three fundamental elements. The new design uses a unique casting process to eliminate welds and eliminates the need for special airfoil coatings. Preliminary design method of a turbopump feed system for. The purpose of this publication is to provide the serious amateur builder with design information. Turbopump design and analysis approach for nuclear thermal rockets shucheng s. Hence, for staged combustion cycle engines turbopumps, a more detail sophisticated analysis is required not. In comparison, the shuttle main engine turbomachinery requires maintenance.
Chapter 1 turbopump of rocket form of a liquid propellant rocket. Key technology for reusable rocket engine turbopump. Which combination of turbopump and backing pump is necessary. Also, you wont find any pictures of the new turbopump. It is necessary to enlarge inducer diameter to improve suction performance of le7a turbopump without the addition of jet pump and boost pump. It was powered by hydrogen peroxide that passed through a potassium permangante catalyst and was separated into water vapor and oxygen. Design and analysis of a high speed, high pressure. Figure 2 sketch of the simulated rocket engine the.
This turbopump was used on several rocket engines, including the navaho g26 engine, the s3d engine aka lr79, used on. Designed lox and methane turbopump assemblies tpas as part of a team designing a 60,000pound thrust expander cycle rocket engine. Nasa has previously tested simple 3dprinted rocket components, such as combustion chambers and fuel injectors, but if the technique is to be practical, it has to cope with more complex items. Building a better rocket engine science mission directorate. The concept design of a split flow liquid hydrogen. The design method is a kind of multidisciplinary optimum design and is formed in two steps. It will be the first booster engine in the world with an expander bleed cycle. The engine and its turbopump were developed by the. The v2 engine was both the worlds first large liquidpropellant rocket engine and the first large rocket engine to use a turbopump. Modification and verification testing of a russian nk33. Loxmethane turbopump design turbo solutions engineering.
This gushing torrent of fuel is driven by a turbopump. Thus, leveraging modern technology to substantially increase the performance of such engines, a singleshaft, radial turbine, centrifugal impeller turbopump has. But today, the privately funded spacecraft company broke all expectations when their dragon capsule fell to a soft landing in the pacific ocean. The first element, the one in blue, is the part that spins. The turbopump can operate at about 50% flow at 36% discharge pressure and 58% of rated speed. A turbopump is a propellant pump with two main components. Shostak4 konstruktorskoe buro khimavtomatiyi, voronezh, russia a. Relies on a turbopump to force propellants from tanks to the combustor tanks kept at lower pressures fuel heated via regenerative cooling process and passed through turbine to drive pumps thrust.
Pdf test of a turbopump fed miniature rocket engine. Design of a silicon microfabricated rocket engine turbopump. This includes a discussion of modern computational fluid dynamic analysis in pump design. A wide variety of design requirementsflow rate, head rise, and fluid characteristics. An open cycle was chosen for the engine system, with a gas generator. Use lng turbopump design during feasibility study 630 gpm at 29. The turbopump fed miniature rocket engine tpfmre is a bipropellant thruster consisting of four subsystems. Multi objective design optimization of rocket engine turbopump turbine naoki tani, akira oyama and nobuhiro yamanishi tani. Turbopump design and analysis approach for nuclear. A microscale turbopump producing a pressure rise of 30 atm for water was designed, as a demonstration of this concept for fluid pressurization in. Singleshaft turbopumps in liquid propellant rocket engines. Ever since spacex in sourced their production there hasnt been any more pictures. The design criteria of inducer which nasa proposed on rocket pumps is shown in fig. The cycle will feature two turbopumps in order to simplify the turbopump design, while on the same time allowing more freedom for a modular exchange of.
By altering the power to the oxidizer turbopump otp, you can control the engine thrust level and, simultaneously, mixture ratio. Turbopumps for gas generator and staged combustion cycle. If a turbopump is designed for a low ultimate pressure, pump stages with various blade angles are used and the gradation is optimized for maximum pumping speeds for hydrogen. Liquid rocket engine turbopump inducers paperback april 28, 2014. Fittje3 1nasa glenn research center, cleveland, ohio 445 2chief.
This project called for the design and development of a reliable turbopump with decreased recurring costs. An initial design of a split flow liquid hydrogen turbopump for the dual expander aerospike nozzle dean upper stage engine was completed. The new design also incorporates silicon nitride bearing elements similar to the. Multi objective design optimization of rocket engine. A brief overview of the basic configurations of pressurefed systems is first given. To power the turbopump, a small amount of fuel is preburned, thus generating hot gases that drive the turbopump, which in turn pumps the rest of the. The number of pieces to be assembled is greatly reduced, compared to a more conventional turbopump. The lubrication concept relies on sacrificial wear of the bearing cage bronze60% teflon, and its transfer from the rolling elements to the raceway surface. It may be up to you to help us amateur experimental rocketeers prgress more in the pump world so here is the literature and help needed to get started. The process of pump design, from a basic performance specification through preliminary design, blade layout and analysis, and design optimization is described. In the designing process, the performance requirements of the turbopump and other. This paper presents a new the integrated design method concept developed to provide. Therefore its rotordynamic behavior must be evaluated during the design stage.
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