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TURBOCHARGER AS TURBO-EXPANDER FOR ORGANIC RANKINE CYCLE

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TURBOCHARGER AS TURBO-EXPANDER FOR ORGANIC RANKINE CYCLE ( turbocharger-as-turbo-expander-for-organic-rankine-cycle )

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Specific Speed Figure 4: Performance Chart of Radial Turbine by Balje (Balje, 1981) (1) (2) 1975). The performance analysis process was widely applied in performance estimation of turbochargers for both steady-state (Serrano, Arnau, Dolz, Tiseira, & Cervelló, 2008) and unsteady flow conditions (Rajoo, Romagnoli, & Martinez-Botas, 2012). The performance model was developed under the assumption of perfect gas, in which the ideal gas equation is applied and specific heat capacity is assumed to be constant at all temperatures (Meitner & Glassman, 1980, 1983; Wasserbauer & Glassman, 1975). In this study, as the performance analysis was conducted in Engineering Equation Solver (EES), the in-built real gas properties of EES is applied to determine the thermodynamic properties of real fluids instead of using the ideal gas law. The fluid behaviour can be predicted at higher accuracy compared to the application of the ideal gas equation. The loss models will not be discussed in detail as the information can be obtained in the relevant sources. 3.1 Passage Loss Passage loss is defined as total fluid flow loss inside the blade passage, including secondary flow loss, mixing flow loss, the blockage loss, and the kinetic energy loss due to growth of a boundary layer along the blade surface (Moustapha, Zelesky, Baines, & Japiske, 2003). Baines’s textbook reported that the initial passage loss model by NASA cannot accurately predict the passage loss for all types of radial turbines under different operating conditions. An improved version of passage loss is presented in his work, which is shown below. (3) The incidence loss model is developed as a function of change in relative tangential velocity energy of the working fluid (Ghosh, Sahoo, & Sarangi, 2011). The fluid approaches the turbine wheel at an angle different from the optimal angle. The optimal relative flow angle is determined based on the empirical formulation below. The incidence loss is then determined as fluid flow loss at any incidence angle other than the optimal flow angle.  m n s h 0.75 is d Dhis0.25 s m  The radial turbine was also chosen for several reasons. Radial turbines are cheaper than axial turbines. The radial turbine is more robust under high blade loading by high density working fluids such as R245fa and stable from the standpoint of rotor-dynamic due to high stiffness (Ventura, Jacobs, Rowlands, Petrie-Repar, & Sauret, 2012). Table 1 shows geometry and overall dimensions of a selected radial turbine (known as TC-1) from a turbocharger for petrol- driven vehicle. Table 1: Basic Dimensions Value of Turbocharger TC-1 Unit Value 222 K Lh 0.681r2  cos2*W2 W1  passage p D rb2W2 h12 Inlet radius Outlet tip radius Outlet hub radius Inlet blade height Total blade height Blade number Inlet blade angle Outlet blade angle at tip Outlet blade angle at hub 3. NUMERICAL MODEL r (mm) 1 r2,tip (mm) r2,hub (mm) bin (mm) btotal (mm) Z 22.3 19.3 6.5 6 18.5 9 tan1,opt  1.98tan1 Z 11.98 C 3.2 Incidence Loss β1,b 0 β2t,b 55 β2h,b 45 3.3 Trailing Edge Loss Off-design performance of radial turbine was first developed in FORTRAN by Glassman as part of the NASA gas turbine program in 1970 (Wasserbauer & Glassman,  te M2 P rZ r (4) (5) W1 sin1 1,opt 2 incidence  W  2  Trailing edge loss is calculated from the relative total pressure loss (Ventura et al., 2012). The relative total pressure loss is proportional to the relative kinetic energy at the rotor exit (Ghosh et al., 2011). The relative total pressure loss is then converted to enthalpy loss coefficient as below (Ventura et al., 2012). (6) 35th New Zealand Geothermal Workshop: 2013 Proceedings 17 – 20 November 2013 Rotorua, New Zealand 2 P 0,rel 2,rel 02,rel Specific Diameter

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