Aerodynamic design and numerical simulation of combined cycle nozzle with small length to height ratio

GE Wenxing; GUI Feng; YUAN Huacheng; HE Mofan; GUO Rongwei

doi:10.11729/syltlx20190142

Volume 34 Issue 6

Dec. 2020

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GE Wenxing, GUI Feng, YUAN Huacheng, et al. Aerodynamic design and numerical simulation of combined cycle nozzle with small length to height ratio[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(6): 8-17. doi: 10.11729/syltlx20190142

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Aerodynamic design and numerical simulation of combined cycle nozzle with small length to height ratio

doi: 10.11729/syltlx20190142

1.
Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Sichuan Gas Turbine Establishment, Aero Engine Corporation of China, Chengdu 610500, China

Received Date: 2019-11-04
Rev Recd Date: 2020-02-17
Publish Date: 2020-12-25

Abstract

Abstract

A preliminary study on the aerodynamic design of the combined cycle nozzle working in the range Ma=0~6.0 with small length to height ratio was carried out under strong geometric restricts. The line of the nozzle was designed by the method of characteristic. The effects of the design Mach number, the three-dimensional lateral expansion angle and the relative position of the two nozzles on the aerodynamic performance were studied. A nozzle aerodynamic design scheme considering both the effective utilization of space and the aerodynamic performance was presented. The numerical simulation results show that reducing the Mach number at the design points can improve the performance of the combined cycle nozzles during the subsonic flight and avoid serious overexpansion of the nozzles. With the increase of the lateral expansion angle, the aerodynamic performance of the nozzle that keeps the exit height unchanged at high Mach number is superior, while the aerodynamic performance of the nozzle at low Mach number decreases seriously. The relative position of the turbine engine and the ramjet nozzle outlet has a great influence on the aerodynamic performance of the transition point, and there is an optimal position layout, which achieves the optimal thrust performance. The thrust coefficient of the combined cycle nozzle is about 0.920 at the designed Mach number. The flow field is smooth transition during the transition mode, when the thrust coefficient is not less than 0.918.
- TBCC,
- nozzle with small length to height ratio,
- numerical simulation,
- transition mode

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References(23)

References

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