Figure from:Numerical Simulation of a Centrifugal Compressor

Figure 6 S.M.Swamy.et.al. Int. Journal of Engineering Research and Application ISSN : 2248-9622, Vol. 7, Issue 6, (Part -3) June 2017, pp.46-53

Related Figures (10)

S.M.Swamy.et.al. Int. Journal of Engineering Research and Application ISSN : 2248-9622, Vol. 7, Issue 6, (Part -3) June 2017, pp.46-53 generation of three dimensional blades was done in order to carry out structural analysis of the blade surfaces the software provided export options to generate computational mesh accounting blade thickness is also explored in static structural analysis package. The blade profiles generated in above software module are imported to template based multi-block structured computational mesh software module called turbo grid. The information related to machine data, profile curves, several inputs required for width factor periodicity production, topology freezing for generation o geometric representation in terms of surface mesh generation with master and slave control points being generated. default orientation of master and slave control points on the blade surfaces are to be moved to obtain better orthogonally between mesh points. After these operations three dimensiona computational mesh generation process for compressor blade with boundary patches, periodic surfaces are created. Schematic diagram of centrifugal compressor setup as shown in fig.1.The geometric model used for the computational simulation of Centrifugal impeller with above specifications with 3mm thickness throughout the blade for generation of three dimensional blades was done as shown in Fig. 2. A single passage of the impeller with inlet at 50mm ahead of the impeller and outlet at a distance of 35mm downstream of impeller is shown in Fig. 3. Casing is designed with 0.7mm clearance throughout the blade height. Three tip clearances of 2.2%, 5.1% and 7.9% of trailing edge blade height are obtained by moving the casing axially. ANSYS CFX 15.0 version software is used for obtaining the solution and standard k-< turbulence model is used for the closure. The computational domain is kept at 50 mm ahead of the eye inlet of the impeller in order to ensure that the inlet boundary conditions are not affected by the back pressure of impeller blade. The blade gen layout with construction features related to wrapper angle, number of blades, angles distribution and blade thickness for