High Performance 3-D Simulation Code for Laser Plasma Accelerators and Plasma Processing of Integrated Circuits, with a Graphical User Interface

Not Available The synergistic design of the combustor, compressor diffuser, and turbine inlet guide vane is proposed to maintain angular momentum (swirl knietic energy) from the compressor rotor discharge while permitting bulk swirl witnin the combustor at relatively high Mach number. This innovation extends a demonstation of the variable residence time (VRT) combustor, which exploited a circumferentially bulk swirling flow within the combustor, to establish a high performance combustion process. Because combustion iwht swirl and gigher Mach number, the last compressor vane row and the first turbine vane are modified to provide less aerodynamic turning and less velocity change, thus reducing losses through all reduced with improved efficiency in support of the IHPTET initiative. phase I work includes combustor rig tests with varying degrees of swirl (0 to 60) and high Mach number (0.2 to 0.6). The rig test results will be used for comprehensive cycle evaluations to quantify the impact from high swirl/Mach number on cycle performance and size. Phase I test and analysis results will demonstrate that reduced losses lead to at least two tofour more points of compressor efficiency and one or two more points of turbine efficiency.