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GA seeks to minimize or maximize the objective function as a combination of perfor mance parameters of the compressor, including pressure ratio and efficiency. The weight o each parameter in this function depends on the design objectives. Given that pressure ratic can be increased using simpler methods such as increasing the compressor diameter comparec to efficiency improvement methods, maximizing efficiency is more emphasized in literature when optimizing centrifugal compressors. Only one or a number of operating points can bi considered in optimizations. Although the second method cited is not very popular, it im: proves the performance of a compressor compared to the base design in the whole range o operation conditions rather than in a single operating point. Equation (1) shows the mass flov averaged efficiency: According to Figure 3, a minor shift is observed in the hub in the beginning of the blades,

Figure 3 GA seeks to minimize or maximize the objective function as a combination of perfor mance parameters of the compressor, including pressure ratio and efficiency. The weight o each parameter in this function depends on the design objectives. Given that pressure ratic can be increased using simpler methods such as increasing the compressor diameter comparec to efficiency improvement methods, maximizing efficiency is more emphasized in literature when optimizing centrifugal compressors. Only one or a number of operating points can bi considered in optimizations. Although the second method cited is not very popular, it im: proves the performance of a compressor compared to the base design in the whole range o operation conditions rather than in a single operating point. Equation (1) shows the mass flov averaged efficiency: According to Figure 3, a minor shift is observed in the hub in the beginning of the blades,

Related Figures (4)

Figure 1. Velocity Contour around compressor volute. Variations in blade profiles should be expressed as multiple interpolations, which can be modified by changing control points used by this optimization method. To create these inter- polations, a 3D model of the impeller was developed in which the impeller was divided into separate parts, and each part was broken into points and estimated with an appropriate inter- polation. The difficulty of grid generation is that it must suit different designs of compressors and impellers with different geometries, which need special treatment.
Figure 1. Velocity Contour around compressor volute. Variations in blade profiles should be expressed as multiple interpolations, which can be modified by changing control points used by this optimization method. To create these inter- polations, a 3D model of the impeller was developed in which the impeller was divided into separate parts, and each part was broken into points and estimated with an appropriate inter- polation. The difficulty of grid generation is that it must suit different designs of compressors and impellers with different geometries, which need special treatment.
In general, the decrease in the total length of the blades causes an efficiency improvement by reducing energy waste, while reducing the area associated with the blades and therefore reducing both the energy transfer from the blade to the flow and the pressure ratio. Simulation results suggest the simultaneous presence of both these effects, i.e., increasing efficiency is accompanied by a minor drop in the pressure ratio. Figure 2. 2D Streamlines around impeller at shroud.
In general, the decrease in the total length of the blades causes an efficiency improvement by reducing energy waste, while reducing the area associated with the blades and therefore reducing both the energy transfer from the blade to the flow and the pressure ratio. Simulation results suggest the simultaneous presence of both these effects, i.e., increasing efficiency is accompanied by a minor drop in the pressure ratio. Figure 2. 2D Streamlines around impeller at shroud.
choke initiates. In this section, a shock wave starting between two blades restricts the mass Figure 4 shows that the maximum Mach numbers emerge near the shroud section where Figure 5 shows high turbulence and disturbed flow fields in the shrouds of optimal design
choke initiates. In this section, a shock wave starting between two blades restricts the mass Figure 4 shows that the maximum Mach numbers emerge near the shroud section where Figure 5 shows high turbulence and disturbed flow fields in the shrouds of optimal design
mass flow cannot exit properly, which causes blockage and instability. The present article proposed a novel approach for optimizing the impellers of centrifugal
mass flow cannot exit properly, which causes blockage and instability. The present article proposed a novel approach for optimizing the impellers of centrifugal
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