Design and analysis of a high speed, high pressure. Ever since spacex in sourced their production there hasnt been any more pictures. In comparison, the shuttle main engine turbomachinery requires maintenance. Multi objective design optimization of rocket engine. The process of pump design, from a basic performance specification through preliminary design, blade layout and analysis, and design optimization is described. Fittje3 1nasa glenn research center, cleveland, ohio 445 2chief. Figure 2 sketch of the simulated rocket engine the. The first element, the one in blue, is the part that spins. The turbopump fed miniature rocket engine tpfmre is a bipropellant thruster consisting of four subsystems.
Shostak4 konstruktorskoe buro khimavtomatiyi, voronezh, russia a. This project called for the design and development of a reliable turbopump with decreased recurring costs. The v2 engine was both the worlds first large liquidpropellant rocket engine and the first large rocket engine to use a turbopump. Liquid rocket engine turbopump inducers paperback april 28, 2014. The concept design of a split flow liquid hydrogen. 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. The engine and its turbopump were developed by the. The number of pieces to be assembled is greatly reduced, compared to a more conventional turbopump. By altering the power to the oxidizer turbopump otp, you can control the engine thrust level and, simultaneously, mixture ratio. Ive drawn this in three colors because a turbopump can be thought of as having three fundamental elements.
In the designing process, the performance requirements of the turbopump and other. Hence, for staged combustion cycle engines turbopumps, a more detail sophisticated analysis is required not. Multi objective design optimization of rocket engine turbopump turbine naoki tani, akira oyama and nobuhiro yamanishi tani. A wide variety of design requirementsflow rate, head rise, and fluid characteristics. 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. A brief overview of the basic configurations of pressurefed systems is first given. Modification and verification testing of a russian nk33. Singleshaft turbopumps in liquid propellant rocket engines. Designed lox and methane turbopump assemblies tpas as part of a team designing a 60,000pound thrust expander cycle rocket engine.
An initial design of a split flow liquid hydrogen turbopump for the dual expander aerospike nozzle dean upper stage engine was completed. 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. A microscale turbopump producing a pressure rise of 30 atm for water was designed, as a demonstration of this concept for fluid pressurization in. Building a better rocket engine science mission directorate. But today, the privately funded spacecraft company broke all expectations when their dragon capsule fell to a soft landing in the pacific ocean. 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. The purpose of this publication is to provide the serious amateur builder with design information. Loxmethane turbopump design turbo solutions engineering. The rocketdyne mark 3 turbopump was a real workhorse of the early space race. Preliminary design method of a turbopump feed system for. Pdf test of a turbopump fed miniature rocket engine. The new design also incorporates silicon nitride bearing elements similar to the. It was guided by an advanced gyroscopic system that sent signals to aerodynamic steering tabs on the fins and vanes in the exhaust.
Design of a silicon microfabricated rocket engine turbopump. This paper presents a new the integrated design method concept developed to provide. The lubrication concept relies on sacrificial wear of the bearing cage bronze60% teflon, and its transfer from the rolling elements to the raceway surface. 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 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.
Chapter 1 turbopump of rocket form of a liquid propellant rocket. Turbopumps for gas generator and staged combustion cycle. A turbopump is a propellant pump with two main components. The new design uses a unique casting process to eliminate welds and eliminates the need for special airfoil coatings. The turbopump can operate at about 50% flow at 36% discharge pressure and 58% of rated speed. Therefore its rotordynamic behavior must be evaluated during the design stage. It was powered by hydrogen peroxide that passed through a potassium permangante catalyst and was separated into water vapor and oxygen. It will be the first booster engine in the world with an expander bleed cycle. Key technology for reusable rocket engine turbopump. Which combination of turbopump and backing pump is necessary. Thus, leveraging modern technology to substantially increase the performance of such engines, a singleshaft, radial turbine, centrifugal impeller turbopump has.
Bni teamed with rocketdyne to design and build a second turbopump for nasas lcbt program. Turbopump design and analysis approach for nuclear. Use lng turbopump design during feasibility study 630 gpm at 29. Single shaft turbopump expands capabilities of upper stage. This includes a discussion of modern computational fluid dynamic analysis in pump design. The reader is taken stepbystep through a worked design. The design method is a kind of multidisciplinary optimum design and is formed in two steps. Turbopump design and analysis approach for nuclear thermal rockets shucheng s. This gushing torrent of fuel is driven by a turbopump. 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. The design criteria of inducer which nasa proposed on rocket pumps is shown in fig.
475 461 727 635 111 1132 1342 1550 180 186 1085 1441 678 208 108 969 1029 810 969 396 1486 528 188 189 1319 1451 1510 372 816 753 345 230 97 181 852 1224 948 290 805 180