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For CO2, the kinematic viscosity is so low that the buildup of the boundary layer in the vaneless space is negligible. The blockage calculated at the impeller outlet is assumed to represent the blockage at the diffuser inlet. The diffuser is modeled very simply as an increase in area, with corresponding losses due to friction, incidence, and mixing of the wake at the outlet. A database of diffuser performance by Runstadler contains the most thorough data on diffuser performance and was used as the diffuser model in the NASA codes [Runstadler, 1969]. However, its use for a real gas resulted in unphysical results. Thus, it was abandoned in favor of a simple model. Diffusers are always vaned diffusers in RGRC. Pipe diffusers are more expensive to manufacture and are covered by a Pratt and Whitney patent [Cumpsty, 2004]. The subroutine AUNGIER will create a vaned diffuser according to the area ratio input by the user and it will orient the vanes such that the incidence angle for the core flow is zero at the design point. It has been named for the source of the diffuser model [Aungier, 2000]. The vanes can be straight or curved. They will be in line with the flow at the design point at position 3 and can curve up to 25 o further at position 4. The vaned diffuser performance is based on the area ratio, which is described by diffuser inlet and outlet passage widths. The axial dimension of the vaned diffuser does not change in RGRC, so the area ratio is the same as the ratio of the arc lengths at the diffuser inlet and outlet. The diffuser performance is calculated by assuming that the flow follows the blade angle at position 4. By calculating the blockage at position 4 and the losses within the diffuser passage, the code iterates the velocity at position 4 until it achieves conservation of mass from position 3 to position 4. The initial guess of the velocity at position 4 is based simply on the area ratio of the vane, but changes in density and blockage cause this value to be incorrect. The blockage at position 4 is calculated as a portion of the flow area by where ππ is given by π΅4=πΎ1+πΎ2 ππ 2β1πΏπ£πππ π€4 ππ =1 ππ3π πππ½4 +1 2 ππ4π πππ½3 Eqn.3-50 Eqn.3-51 and πΎ1and πΎ2 are empirical constants determined from the diffuser divergence angle, ππΆ, and the blade loading parameter, πΏ. These are defined in terms of the average blade-to-blade velocity difference, Ξπ. πΎ1 =0.2 1β1/πΆπΏπΆπ Eqn.3-52 68PDF Image | Supercritical Carbon Dioxide Cycle Analysis
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