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where h2,st and h1,st represent the static enthalpies of the fluid at the impeller inlet and outlet respectively. The letter U represents blade speed and W is the relative speed of the fluid. Subscripts indicate inlet at the Root Mean Square (RMS) radius (1) or outlet (2). The Euler turbomachinery equation is used directly in RGRC to calculate the static enthalpy rise produced by the impeller. Further rise in static enthalpy is achieved by pressure recovery in diffusers, where the dynamic pressure, 1ā2Ļv2, is reduced and static pressure rises as the flow area expands. Mean-line codes treat the flow in a compressor by modeling the behavior of the fluid at the mean streamline, the surface along the RMS radius of the blade passage. Mean-line compressor codes can be used to develop initial sizing, design, and performance estimates for compressors. In fact, these methods are typically more accurate for determining off-design performance than more advanced computational fluid dynamics (CFD) codes due to their empirical nature [Aungier, 2000]. The mean stream line method was used to improve on existing compressor codes to achieve some understanding of how compressors will perform in an S-CO2 recompression cycle. Existing codes available to MIT did not produce results consistent with themselves and they were very difficult to use and manipulate. These codes were adjusted NASA codes known as CCD and CCODP, which had been altered to work for supercritical CO2. The code structure made editing very tricky. Several remaining ideal-gas assumptions were not appropriate for a real gas compressor. These assumptions persisted despite the fact that real gas property subroutines were included in the codes. Therefore, effort was needed to produce an improved mean-line real gas compressor code. 3.3 Real Gas Radial Compressor (RGRC) Code 3.3.1 Issues with Earlier Codes CCDS/CCODS and Motivation for RGRC Development The NASA mean line centrifugal compressor codes were adjusted by Yifang Gong of the MIT Gas Turbine Laboratory (GTL) to operate with CO2 near the critical point [Hejzlar et al., 2007] These codes consisted of a design code, CCD, and an off-design code, CCODP. They had originally been developed at the NACA Lewis Flight Laboratory, primarily by Jerry Wood [Wood, 1995]. After updates for S-CO2 by Gong, they were renamed CCDS and CCODS, with the āSā added for S-CO2. The CCD/CCODP input data requires the user to choose some basic parameters, but most of the geometry of the compressor is determined by the code in a complicated iterative process. The NASA codes rely on correlations and experimental diffuser data for air and its calculations 50PDF Image | Supercritical Carbon Dioxide Cycle Analysis
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