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Effect of Core Flow Inlet Swirl Angle on Performance of Lobed Mixing Exhaust System

Published online by Cambridge University Press:  16 March 2016

Y. Xie ,
C. Zhong ,
D.-F. Ruan ,
K. Liu  and
B. Zheng
Y. Xie*
Affiliation:
The State Key Laboratory of Mechanical TransmissionChongqing UniversityChongqing, China School of Automotive EngineeringChongqing UniversityChongqing, China
C. Zhong
Affiliation:
School of Automotive EngineeringChongqing UniversityChongqing, China
D.-F. Ruan
Affiliation:
The State Key Laboratory of Mechanical TransmissionChongqing UniversityChongqing, China School of Automotive EngineeringChongqing UniversityChongqing, China
K. Liu
Affiliation:
School of Automotive EngineeringChongqing UniversityChongqing, China
B. Zheng
Affiliation:
School of Automotive EngineeringChongqing UniversityChongqing, China
*
*Corresponding author ([email protected])
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Abstract

Geometric model of a lobed mixing exhaust system is created and its flow field is simulated by using the steady Reynolds Averaged Navier-Stokes (RANS) equations under the condition of different core flow inlet swirl angles. According to the numerical simulation results, due to the guidance effect of the lobe parallel side wall, the structure and vorticity of streamwise vortices change little near the lobe exit with inlet swirl angle, and it is the same with the thermal mixing efficiency. As the flow develops, although the inlet swirl angle has limited influence on the streamwise vorticity, it greatly affects the structure of streamwise vortices. It causes the thermal mixing efficiency to increase with the swirl angle. As for the total pressure recovery coefficient, it falls slightly when the inlet swirl strengthens. At the nozzle exit, the total pressure recovery coefficient of CFISA = 30° model is 0.5% lower than CFISA = 0° model. Moreover, as the inlet swirl strengthens, the thrust fall of lobed mixing exhaust system gradually accelerates, especially when the inlet swirl angle is over 15°.

Keywords

Lobed mixing exhaust systemCore flow inlet swirl anglePerformance of mixing exhaust system
Type
Research Article
Information
Journal of Mechanics , Volume 32 , Issue 3 , June 2016 , pp. 325 - 337
Copyright
Copyright © The Society of Theoretical and Applied Mechanics, R.O.C. 2016 

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References

1.Skebe, S. A., Paterson, R. W. and Baber, T. J., “Experimental Investigation of Three-Dimensional Forced Mixer Lobe Flow Field,” 1st AIAA/ASME/ASCE/SIAM/APS National Fluid Dynamics Congress, U.S.A. (1988).Google Scholar
2.Povinelli, L. A., Anderson, B. H. and Gerstenmaier, W., “Computation of Three-dimensional Flow in Turbofan Mixer and Comparison with Experimental Data,” 18th Aerospace Sciences Meeting, U.S.A. (1980).Google Scholar
3.Paterson, R. W., “Turbofan Mixer Nozzle Flow Field-A Benchmark Experimental Study,” Journal of Engineering for Gas Turbines and Power, 106, pp. 692–698 (1984).CrossRefGoogle Scholar
4.Eckerle, W. A., Sheibani, H. and Awad, J., “Experimental Measurement of the Vortex Development Downstream of a Lobed Forced Mixer,” Journal of Engineering for Gas Turbine and Power, 114, pp. 63–71 (1992).CrossRefGoogle Scholar
5.Werle, M. J. and Paterson, R. W., “Flow Structure in a Periodic Axial Vortex Array,” 25th AIAA Aerospace Sciences Meeting, U.S.A. (1987).Google Scholar
6.Elliott, J. K., et al., “Computational and Experimental Studies of Flow in Multi-lobed Forced Mixers,” 28th AIAA/SAE/ASME Joint Propulsion Conference, U.S.A. (1992).Google Scholar
7.Xie, Y. and Liu, Y. H., “Numerical Investigation of Lobe Spacing Ratio on Performance of Forced Mixer Nozzle,” Heat Transfer-Asian Research, 40, pp. 593–607 (2011).CrossRefGoogle Scholar
8.Xie, Y. and Liu, Y. H., “Numerical Investigation of Lobe Penetration Angle on Performance of Forced Mixer Nozzle,” 10th International Congress of Fluid Dynamic, Egypt (2010).Google Scholar
9.Xie, Y. and Liu, Y. H., “Numerical Investigation of Lobe Length on Performance of Lobed Forced Mixer Nozzle,” The Proceedings of 2010 Asia-Pacific International Symposium on Aerospace Technology, P.R.China (2010).Google Scholar
10.Presz, W. M., Reynolds, G. and Mccormick, D. C., “Thrust Augment Using Mixer-ejector-diffuser Systems,” 32nd Aerospace Sciences Meeting and Exhibit, U.S.A. (1994).Google Scholar
11.Zhang, J. Z., Li, L. G., Gao, C. and He, W. B., “An Experimental Study on a Lobed Nozzle of an Infrared Suppression System,” Journal of Aerospace Power, 12, pp. 212–214 (1997).Google Scholar
12.Presz, W. M., “Mixer/ejector Noise Suppressors,“ 27th AIAA/SAE/ASME/ASEE Joint Propulsion Conference, U.S.A. (1991).Google Scholar
13.Lu, H. Y., Ramsay, J. W. and Miller, D. L., “Noise of Swirling Exhaust Jets,” AIAA Journal, 15, pp. 642–646 (1977).CrossRefGoogle Scholar
14.Kozlowski, H. and Larkin, M., Energy Efficient En gine-exhaust Mixer Model Technology Report, NASA Contractor Report, U.S.A. (1984).Google Scholar
15.Cooper, N. J., Merati, P. and Hu, H., “Numerical Simulation of the Vortical Structures in a Lobed Jet Mixing Flow,” 43rd AIAA Aerospace Sciences Meeting and Exhibit, U.S.A. (2005).Google Scholar
16.Hu, H., Saga, T. and Kobayashi, T., “Investigation of the Vortex Structures Downstream of a Lobed Nozzle by Mean of Dual-plane Stereoscopic PIV,” 4th International Symposium on Particle Image Velocimetry, Germany (2001).Google Scholar
17.Frost, T. H., “Practical Bypass Mixing Systems for Fan Jet Aero-engines,” Aeronaut Quarterly, 17, pp. 141–161 (1966).CrossRefGoogle Scholar
18.Xie, Y. and Liu, Y. H., “A Modified Thermal Mixing Efficiency and Its Application to Lobed Mixer Nozzle for Aero-Engines,” Heat Transfer Research, 42, pp. 317–335(2011).CrossRefGoogle Scholar