The requirements of higher performance for the Space Shuttle Main Engine (SSME) and future space transportation earth-to-orbit propulsion systems dictate the use of efficient liquid rocket engines with engine cycles that invariably require lightweight, high-pressure, hot-gas ducts and manifolds that exhibit uniform flow, low turbulence levels, and minimal pressure drop characteristics. This study, using an extensively modified, full-scale SSME hot-gas manifold (HGM), established a detailed aerodynamic data base to support development of an advanced, threedimensional, fluid-dynamic analysis computer model. In addition, the advanced SSME hot-gas manifold design used in this study demonstrated improved flow environment (uniformity) in the fuel side turbine exit and transfer duct exit regions.Major modifications were incorporated in the full-scale HGM flow test article model using two large transfer ducts on the fuel turbine side of the HGM in place of the three small transfer ducts in the present design. Other model features included an increase in the flow areas downstream of the 180-degree turn and in the fishbowl regions. Tests were conducted at a Rockwell International blowdown facility using ambient temperature, high-pressure air that simulated a range of Reynolds numbers from 20 to 60 percent of the SSME rated power level. Detailed steady-state pressure measurement surveys of the flow field on the fuel side of the hot-gas manifold were conducted. Some highfrequency pressure measurements were included to quantify the turbulent nature of the flow in a qualitative https://ntrs.nasa.gov/search.jsp?R=19850018587 2018-05-11T10:01:59+00:00Z the current design.
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