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Further, it should be taken from 60to 65 °for better design.įor the backswept impellers, the ratio of the relative velocities should be increased for betterment in the design. The stability of the diffuser strongly depends on α c, 2and for both vaneless and vaned diffusers, α c, 2 ≤ 70 °. To meet the above limiting condition, the de Haller impeller ratio should be W 2 W Sh, 1 > 0.75. Separation of the flow in the passages of the impeller should be minimized so that the losses are minimized. The following conditions for the design may be considered as limiting conditionsĪt the inlet of the impeller, very high relative velocity of the shroud W sh, 1should be avoided. The impeller design is the basic and major vital part of the design of the compressor. Velocity triangles of impeller for a centrifugal compressor. Final conclusions are summarized in Section 6. Further, a case study is discussed in detail in Section 4, the corresponding results and discussions are presented in Section 5. In this chapter, a strong attempt is made to enumerate the detailed procedure of the centrifugal compressor in Section 2, concepts and basics of Numerical Schemes in Section 3. Blade topology requires adaptation of a cautious design procedure to achieve the designated pressure rise while minimizing aero-thermodynamic losses in order to run and achieve design pressure ratios and design efficiencies. Stator blade row diffuses the flow, thus reducing absolute velocity component and elevating static pressure. Energy is added in the rotor blade section, increasing the total pressure and absolute component of flow velocity. Various compressor stages achieve gradual increase in the stagnation-to-flow pressure contributed by flow diffusion. The cognitive research and development of compressors is directed toward achieving a higher pressure ratio, higher efficiency, and reduced structural weight of compressor and the engine as well. Consequently, the polytropic efficiency, total-to-total efficiency, stagnation pressure ratio at a fixed rotational speed, and the overall design and aero-thermodynamic performance of the centrifugal compressor are validated.Ĭentrifugal compressors find usage over wide range of propulsion applications and are regarded as one among the key air-breathing propulsive engine components. Finally, a detailed three-dimensional numerical simulation was performed using Reynolds-averaged Navier-Stokes equations based on finite volume discretization method (RANS-FVDM) scheme. An optimum grid size was well validated by carrying out computational analysis with three different mesh sizes within the same framework. A mean-line design methodology was implemented to configure sizing of the compressor. In this chapter, a strong attempt is made to address the above-cited technical issues to achieve an optimized design and performance of a centrifugal compressor with backward swept blade profile producing total pressure ratio of 5.4 with an ingested mass flow rate of 5.73 kg/s. The aero-thermodynamic design and performance of a compressor need to conquer many vital challenges like it is a gas-driven turbo-machinery component, involvement of extensive iterative process for the convergence of the design, enormous design complexity due to three-dimensional flow phenomena, and multiflow physics embedded within a dynamic state-of-the-art.