Numerical Investigation of Turning Diffuser Performance by Varying Geometric and Operating Parameters

Normayati Nordin; Vijay R. Raghavan; Safiah Othman; Zainal Ambri Abdul Karim

doi:10.4028/www.scientific.net/AMM.229-231.2086

Paper Titles

An Improved Slope Classification Mapping Method
p.2069

Numerical Simulation of Pressure Limits of Gas Storage in North Area of Lamadian Oilfield
p.2073

Analysis of LDMOS for Effect of Fingers, Device-Width and Inductance (Load) on Reverse Recovery
p.2077

Numerical Investigation of Turbulence Models for Free Jet Flow
p.2082

Numerical Investigation of Turning Diffuser Performance by Varying Geometric and Operating Parameters
p.2086

Experimental and Numerical Investigation on Flowfield of Film Cooling from Multiple Holes
p.2094

Determination of the Significance of Tolerance Parameters on Robot Performance Using Taguchi’s Tolerance Design Experiment
p.2100

Numerical Simulation of Combustion for Freely Falling Gelled Fuel Droplets under Normal Gravity Conditions
p.2106

Modeling and Simulation of System Dynamics for Spacecraft Propulsion System
p.2112

HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 229-231Numerical Investigation of Turning Diffuser...

Numerical Investigation of Turning Diffuser Performance by Varying Geometric and Operating Parameters

Abstract:

This paper presents a numerical investigation of pressure recovery and flow uniformity in turning diffusers with 90^o angle of turn by varying geometric and operating parameters. The geometric and operating parameters considered in this study are area ratio (AR= 1.6, 2.0 and 3.0) and inflow Reynolds number (Re_in=23, 2.653E+04, 7.959E+04, 1.592E+05 and 2.123E+05). Three turbulence models, i.e. the standard k-e turbulence model (std k-e), the shear stress transport model (SST-k-W) and the Reynolds stress model (RSM) were assessed in terms of their applicability to simulate the actual cases. The standard k-e turbulence model appeared as the best validated model, with the percentage of deviation to the experimental being the least recorded. Results show that the outlet pressure recovery of a turning diffuser at specified Re_in improves approximately 32% by varying the AR from 1.6 to 3.0. Whereas, by varying the Re_in from 2.653E+04 to 2.123E+05, the outlet pressure recovery at specified AR turning diffuser improves of approximately 24%. The flow uniformity is considerably distorted with the increase of AR and Re_in. Therefore, there should be a compromise between achieving the maximum pressure recovery and the maximum possible flow uniformity. The present work proposes the turning diffuser with AR=1.6 operated at Re_in=2.653E+04 as the optimum set of parameters, producing pressure recovery of C_p=0.320 and flow uniformity of su=1.62, with minimal flow separation occurring in the system.

You might also be interested in these eBooks

View Preview

Info:

Periodical:

Applied Mechanics and Materials (Volumes 229-231)

Pages:

2086-2093

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.229-231.2086

Citation:

Cite this paper

Online since:

November 2012

Authors:

Normayati Nordin, Vijay R. Raghavan, Safiah Othman, Zainal Ambri Abdul Karim

Keywords:

Computational Fluid Dynamics (CFD), Flow Uniformity, Geometric Parameter, Operating Parameters, Pressure Recovery, Turning Diffuser

Export:

RIS, BibTeX

Price:

Permissions:

Request Permissions

References

[1] R.W. Fox and S.J. Kline, Flow regime data and design methods for curved subsonic diffusers, J. Basic Eng. ASME, vol. 84, pp.303-312, (1962).

DOI: 10.1115/1.3657308

Google Scholar

[2] C.J. Sagi and J.P. Johnson, The Design and Performance of Two-Dimensional, Curved Diffusers, J. Basic Eng. ASME, vol. 89, pp.715-731, (1967).

Google Scholar

[3] G. Guohui and B.R. Saffa, Measurement and computational fluid dynamics prediction of diffuser pressure-loss coefficient, Applied Energy, vol. 54(2), pp.181-195, (1996).

DOI: 10.1016/0306-2619(95)00078-x

Google Scholar

[4] B. Majumdar and D.P. Agrawal, Flow characteristics in a large area ratio curved diffuser, Proc. Instn. Mech. Engrs., vol. 210, p.65, (1996).

Google Scholar

[5] E.G. Tulapurkara, A.B. Khoshnevis and J.L. Narasimhan, Wake boundary layer interaction subject to convex and concave curvatures and adverse pressure gradient, Exp. In Fluids, vol. 31, pp.697-707, (2001).

DOI: 10.1007/s003480100337

Google Scholar

[6] C.K. Nguyen, T.D. Ngo, P.A. Mendis and J.C.K. Cheung, A flow analysis for a turning rapid diffuser using CFD, J. Wind Eng., vol. 108, pp.749-752, (2006).

Google Scholar

[7] T.P. Chong, P.F. Joseph and P.O.A.L. Davies, A parametric study of passive flow control for a short, high area ratio 90 deg curved diffuser, J. Fluids Eng., vol. 130, (2008).

DOI: 10.1115/1.2969447

Google Scholar

[8] W.A. El-Askary and M. Nasr, Performance of a bend diffuser system: Experimental and numerical studies, Computer & Fluids, vol. 38, pp.160-170, (2009).

DOI: 10.1016/j.compfluid.2008.01.003

Google Scholar

[9] Y.C. Wang, J.C. Hsu and Y.C., Lee, 9], "Loss characteristics and flow rectification property of diffuser valves for micropump applications, Int. J. of Heat and Mass Transfer, vol. 52, pp.328-336, (2009).

DOI: 10.1016/j.ijheatmasstransfer.2008.06.010

Google Scholar

[10] J.A. Bourgeois, R.J. Martinuzzi, E. Savory, C. Zhang and D. A. Roberts, Assessment of turbulence model predictions for an aero-engine centrifugal compressor, J. Turbomachinery, vol. 133, pp.1-15, (2010).

DOI: 10.1115/1.4001136

Google Scholar

[11] W.P. Jones, B.E., Launder, The calculation of low-reynolds number phenomena with a two equation model of turbulence, Int. J. Heat Mass Transfer, vol. 6, pp.1119-1130, (1973).

DOI: 10.1016/0017-9310(73)90125-7

Google Scholar

[12] M.K. Gopaliya, M. Kumar, S. Kumar, S.M. Gopaliya Analysis of performance characteristics of S-Shaped diffuser with offset, Aerospace Science and Technology, vol. 11, pp.130-135, (2007).

DOI: 10.1016/j.ast.2006.11.003

Google Scholar

[13] I.H. Ibrahim, E.Y.K. Ng, K. Wong and R. Gunasekaran, Effects of centerline curvature and cross-sectional shape transitioning in the subsonic diffuser of the f-5 fighter jet, J. Mechanical and Science Technology, vol. 22, pp.1993-1997, (2008).

DOI: 10.1007/s12206-008-0744-7

Google Scholar

[14] J.H. Bell and R.D. Mehta, Contraction design for low-speed wind tunnels, NASA 177488, Contract NAS2-NCC-2-294, (1988).

Google Scholar