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RADIAL TURBINE GLOBAL DESIGN CODE Radial Turbine Global Design is an engineering-based design tool, that has been implemented in MATLAB environment to allow a preliminary design of radial gas turbines for different applications. The only limit of MATLAB software is that there are no thermodynamic tools already implemented, therefore it was necessary to use the Coolprop libraries [10] to calculate the thermodynamic properties of a wide variety of fluids, such as density, the specific heats, cp and cv, their ratio γ and the viscosity, 𝜇. RTGD is based on an automated model that allows determining several turbine’s features, including geometry and performance, considering few simple inputs. FIGURE 3. RTGD Diagram The RTGD [11] it has been organizing in two different parts, in which the second is a consequence of the first and cannot be a standalone code. In the first part the turbine geometry and velocity triangles are computed, while in the second part will analyze, using several loss models and correlations, the efficiency that the geometry already produced in the first can achieve. The detailed estimation of the rotor geometric parameters is necessary in order to improve the three-dimensional blade shape through well-defined models, in order to minimize the losses and to maximize the stage efficiency. Regarding the stator nozzles losses have been provided in terms of the total pressure drop and total temperature. Running the code using different input parameters allows appreciating their impact on the achievable performance changes. This feature can be clearly considered one of the most important goals of this work, because it can provide an important information for a further design strategy. The main advantage of the RTGD compared to other codes, such as the NASA code RIFTUD [5], used as a comparison in this work, consists in the request of only seven input parameters unlike RIFTUD which requires 26, some of which are specific of the stator and rotor geometry. Moreover, RTGD is able to estimate different types of rotor loss, which will be discussed in detail in the next section, necessary for turbine performance prediction. Loss Models In this part, the different types of losses will be analyzed. The losses in the rotor are associated with many complex phenomena that make the extraction of power from the rotor degraded with respect to what is prescribed by the Euler equation. The losses analyzed in this work are estimated in order to determine the radial turbine performance and the effective work done by the rotor blades, and therefore the developed power. They will be implemented six different types of losses: incidence, passage, tip- clearance, trailing edge, windage losses and kinetic-energy loss at the rotor exit. The rotor is the main element to be investigated, which is strongly integrated within the turbine, therefore, the radial turbine rotor design represents the most complex element to be realized. The cause of this complexity depends on the three-dimensional fluid-dynamic interactions between the stator and the rotor and between the rotor and casing, which are not entirely known. OUTPUT - Efficiency - Stator - Stator - Enthalpy - Pressure Ratio and and Rotor Rotor Pressure Temperature Discharge Discharge - Rotor ▪ Blade Geometry : Numbers ▪ Inlet ▪ Exit ▪ Exit Hub Rotor Shroud Radius Radius , Radius ▪ Outlet Thickeness Blade ▪ Inlet Blade and Exit Height INPUT - Inlet Temperature - Inlet pressure - Number of revolutions [rpm] - Power - Mass Flow Rate - Specific Speed - Fluid Properties by CoolProp: ▪ Inlet and outlet Density ▪ Hot gas characteristics (cp, γ) RTGD 020097-4PDF Image | Radial turbine preliminary design and performance prediction
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