(PDF) Interactive Aerospace Engineering and Design | jack nel - netflixlogins.orgInternational Journal of Computer Applications 16 , November In this paper, a new method and modern for Preliminary design and optimization mass turbopump in a liquid propellant rocket engine LPRE using the gradient algorithm has been developed. The cycle type of LPRE is open cycle and configuration of turbopump feed system consists of a impulse Turbine at the end of the shaft, an oxidizing centrifugal pumps and a fuel pump centrifugal that have been each other back-to-back on a common shaft. The proposed approach is based on four characteristics, optimal power system performs turbopump. These four characteristics are to achieve the desired characteristic of cavitation in pumps, in particular pump-balanced oxidizer turbine production capacity and total power consumption of the rotor pump-structures and also to estimate the mass of the turbopump feeding system as a result of this process. The design of the input parameters for the preliminary design of each component is determined and then use algorithms that are designed for the pump and turbine box design, preliminary design done.
Space Propulsion Analysis and Design
Space propulsion analysis and design
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Johnson and D. Please re-enter recipient e-mail address es. The design has been blessed by Niven and Pournelle. Conway.
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