Radial turbine preliminary design and performance prediction

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Radial turbine preliminary design and performance prediction ( radial-turbine-preliminary-design-and-performance-prediction )

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๐œ“ = ๐›ฅh0 (1) ๐‘ข2 4 ๐œ‘ = ๐‘๐‘š5 (2) ๐‘ข5 Efficiency can be plotted as a function of these two coefficients, it is observed that the maximum efficiency occurs when the loading coefficient is in the range of 0.9-1.0 and the flow coefficient is between about 0.2-0.3. FIGURE 2. Efficiency: Loading and Flow Coefficients [1] Radial turbines have been extensively investigated, both experimentally and numerically, at NASA Lewis Research Centre, starting in the mid1960s. The first analytical study on the radial turbine performance was carried out by Rohlik in order to determine the optimum geometry. In these introductory notes, will be illustrated primarily on the various, one-dimensional computer models that have been developed in the past. Reference [2] describes a computer code, based on the model reported in [3] that can be used to predict the off-design performance of a Radial Inflow Turbine. An improved version of the computer code described in [2] is presented in [4]: it features better loss models than those implemented in [3] and also allows to account for trailing edge blockage and to compute flow conditions for pressure ratios at or beyond stator and/or rotor chocking. A parallel development beside the program described in [2, 4], NASA also released the RIFTUD (Radial Inflow Turbine Design) [5] code. RIFTUD is a design code based on Rohlikโ€™s model [6] that produces an โ€œoptimalโ€ geometry for a prescribed mass flow and torque. RIFTUD features a slightly different flow-model than the one used in [2, 4], it uses a multiple stream tube analysis at the rotor outlet. This feature has subsequently [7] been merged into the off-design code of references [2, 4], thus giving rise to the RTOD (Radial Turbine Off-Design) code [7]. RTOD is still being distributed by NASA today [8], although its use is limited to US citizens. The purpose of this paper is the development of new methodologies for the optimal design of radial turbines, a tool called RTGD has been developed, which uses mathematical models to simplify the turbine design considering the flow losses in the rotor. Regarding loss phenomena have been implemented six different types of losses: incidence, passage, tip-clearance, trailing edge, windage losses and kinetic-energy loss at the rotor exit. Contrary to what was expected, not much data on real radial turbines has been found in the literature, therefore RTGD has been validated considering the only two cases found, concerning a turbine that uses Air [9] as the working fluid and another that uses Argon [4]. In the case of the turbine Argon, RTGD it was compared with the RIFTUD code. 020097-3

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