Abstract: The current trend towards increased payloads in the U.S. Launching industry requires the utilization of a larger number of engines and/or the development of new engines of increased performance, in order to provide the new rocket vehicles with the desired thrust. The most performant rocket engines able to match the industry requirements are liquid propellant engines utilizing turbopumps to achieve high pressures in their thrust chambers required for maximized thrust. A review of various engine cycles and their configuration will provide a basic understanding of the existing and future designs. Following the perspective of the recent development programs, such as RS-68 (Delta IV), MB-XX (Technology Demonstrator) and J-2X (NASA) specific trends and design challenges are examined, together with a brief overview of the Space X Merlin 1C/1D programs (Falcon 9, 9 Heavy). The difficulties in the analysis associated with the design high performance, lightweight turbopumps are presented in the context of specific processes targeting the prediction of stresses induced by High Cycle Fatigue.
Host: Prof. Eckart Meiburg