Hostname: page-component-6bf8c574d5-rwnhh Total loading time: 0 Render date: 2025-02-15T00:59:50.106Z Has data issue: false hasContentIssue false
  • English
  • Français

Infrared radiation characteristics of an aero-engine binary plug nozzle with various slot cooling configurations

Published online by Cambridge University Press:  12 February 2025

Y. Song Open the ORCID record for Y. Song [Opens in a new window] ,
Q. Yang ,
Y. Shi Open the ORCID record for Y. Shi [Opens in a new window] ,
H. Xiang Open the ORCID record for H. Xiang [Opens in a new window]  and
L. Chen
Y. Song*
Affiliation:
School of Energy and Power Engineering, Xi’an Jiaotong University, Xi’an 710049, China
Q. Yang
Affiliation:
School of Power and Energy, Northwestern Polytechnical University, Xi’an 710129, China
Y. Shi
Affiliation:
School of Power and Energy, Northwestern Polytechnical University, Xi’an 710129, China
H. Xiang
Affiliation:
School of Power and Energy, Northwestern Polytechnical University, Xi’an 710129, China
L. Chen
Affiliation:
School of Power and Energy, Northwestern Polytechnical University, Xi’an 710129, China
*
Corresponding author: Y. Song; Email: [email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

For binary plug nozzle, the plug cone is exposed to high-temperature mainstream flow, making it one of the nozzle’s high-temperature components. This paper uses the Realizable k-ε turbulence model and the reverse Monte Carlo method to numerically investigate the aerodynamic and infrared radiation characteristics of the plug nozzle. Various slot cooling configurations were adopted to study the nozzle’s infrared radiation in detail. Results indicate that compared to the baseline nozzle, the plug nozzle’s performance is slightly reduced due to the decrease in effective area of flow over the plug cone. Introducing slot cooling at the rear edge provides significant infrared suppression benefits at low detection angles and notably reduces infrared radiation discrepancy with baseline nozzle at high detection angles. The cooling air from slots causes the nozzle jet to exhibit a ‘thermal layered’ feature. With the same total coolant mass flow, the ‘leading edge + trailing edge’ cooling configuration can lower the area-averaged wall temperature of the plug cone by 5.5% – 12.3%. However, its infrared radiation intensity at each detection angle on the pitch detection plane is higher than that of the ‘trailing edge’ configuration. The significance of leading-edge cooling is focused more on thermal protection for the plug. Thus, it is essential to balance coolant mass flow distribution between infrared radiation suppression and thermal protection.

Keywords

aero-engineplug nozzleslot coolingcooling configurationaerodynamic performanceinfrared radiation characteristicsinfrared stealth
Type
Research Article
Information
The Aeronautical Journal , First View , pp. 1 - 22
Check for updates
Copyright
© The Author(s), 2025. Published by Cambridge University Press on behalf of Royal Aeronautical Society

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Mahulikar, S.P., Sonawane, H.R. and Arvind Rao, G. Infrared signature studies of aerospace vehicles, Prog Aerosp Sci., 2007, 43, pp 218–245. doi: 10.1016/j.paerosci.2007.06.002.CrossRefGoogle Scholar
Shan, Y., Zhang, J. and Pan, C. Numerical and experimental investigation of infrared radiation characteristics of a turbofan engine exhaust system with film cooling central body, Aerosp Sci Technol., 2013, 28, pp 281–288. doi: 10/f44hwx CrossRefGoogle Scholar
Chen, X. and Zhang, X. Coupled analysis of the film-cooling and infrared characteristics of an Axisymmetric Vectoring Exhaust Nozzle, in 2015 IEEE Aerospace Conference, IEEE, New York, pp 1–8. 2015.CrossRefGoogle Scholar
Liu, J. and Ji, H. Experimental investigation on infrared signatures of Axisymmetric Vectoring Exhaust Nozzle with film cooling and low-emissivity coating, J Eng Gas Turbines Power-Trans ASME., 2018, 140, p 091203. doi: 10/gtm2kn CrossRefGoogle Scholar
Gao, X., Yang, Q.Z., Zhou, H. and He, J.N. Numerical simulation on the infrared radiation characteristics of S-shaped nozzles, Appl Mech Mater., 2014, 482, pp 282–286. doi: 10/gtm2kp CrossRefGoogle Scholar
Maiden, D.L. and Petit, J.E. Investigation of two-dimensional wedge exhaust nozzles for advanced aircraft, J Aircr., 1976, 13, pp 809–816. doi: 10/fhhg7d CrossRefGoogle Scholar
Zebbiche, T. Supersonic plug nozzle design, in 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, American Institute of Aeronautics and Astronautics, Tucson, Arizona, p 4490. 2005.CrossRefGoogle Scholar
Chutkey, K., Vasudevan, B. and Balakrishnan, N. Analysis of annular plug nozzle flowfield, J Spacecr Rockets., 2014, 51, pp 478–490. doi: 10/f5wns3 CrossRefGoogle Scholar
Chutkey, K., Vasudevan, B. and Balakrishnan, N. Flow and performance analysis of annular cluster truncated plug nozzle, J Propuls Power., 2016, 32, pp 1442–1453. doi: 10/gt3hhd CrossRefGoogle Scholar
Chutkey, K., Vasudevan, B. and Balakrishnan, N. Flow investigation of linear cluster plug nozzle, J Spacecr Rockets., 2016, 53, pp 39–45. doi: 10/f8fqgt CrossRefGoogle Scholar
Dumitrescu, O., Gherman, B. and Dragan, V. Study of full and truncated aerospike nozzles on performances at different working conditions. IOP Conf Ser Mater Sci Eng., 2018, 400, p 042017. doi: 10/gtm29b CrossRefGoogle Scholar
Resta, E., Di Cicca, G., Ferlauto, M. and Marsilio, R. Thrust vectoring using differential throttling in axisymmetric Aerospike nozzle. In AIAA SCITECH 2024 Forum. Orlando, FL: American Institute of Aeronautics and Astronautics, p 1617. 2024.Google Scholar
Zhang, Y., Cheng, M., Liu, X., Rong, G., Sheng, Z., Shen, D., Wu, K. and Wang, J. The influence of plug nozzle and Laval nozzle on the flow field and performance of non-premixed rotating detonation combustor, Phys Fluids., 2024, 36, p 056107. doi: 10/gt33m2 CrossRefGoogle Scholar
Zaman, K.Q. and Fagan, A.F. Flow, noise and thrust of supersonic plug nozzles. In AIAA SCITECH 2024 Forum. Orlando, FL: American Institute of Aeronautics and Astronautics, p 2305. 2024.Google Scholar
Chen, L.-L., Yang, Q.-Z., Chen, L.-H. and Shi, Y.-Q. Numerical Simulation of Radar Scattering Characteristics of Axisymmetric Plug Nozzle, Tuijin JishuJ Propuls Technol., 2018, 39, pp 86–91. doi: 10/gs4fmw Google Scholar
Song, Y., Yang, Q.-Z., Gao, X., Shi, Y.-Q. and He, Y.-B. Electromagnetic scattering characteristics of binary plug nozzle with coating medium at different part, Tuijin JishuJ Propuls Technol., 2022, 43. doi: 10/gs4fmt Google Scholar
Cheng, W. Accurate numerical solution of infrared radiation signature from aircraft plume, J. Thermophys. Heat Transf., 2023, 37, pp 41–50. doi: 10/gt3hgf CrossRefGoogle Scholar
Shi, J., Zhou, L., Xu, J., Shi, J. and Wang, Z. Experimental study on infrared radiation characteristics and matching performance of low-observable nozzles, J Propuls Power., 2024.doi: 10/gt3hfs CrossRefGoogle Scholar
Wang, X., Duan, Q., Jin, W. and Hu, C. Research on the cooling method of the plug cone in axisymmetric plug vector nozzle. In 3rd International Conference on Mechanical, Aerospace and Automotive Engineering (CMAAE 2023). Institution of Engineering and Technology, Nanjing, China, 2023, pp 168–174.CrossRefGoogle Scholar
Ma, Z., Zhang, B. and Bai, Y. Investigation on the influence of film cooling structure on the flow and heat transfer characteristics of Axisymmetric plug nozzle, Symmetry., 2024, 16, p 689. doi: 10/gt33m7.CrossRefGoogle Scholar
Chen, J., Shan, Y., Zhang, X. and Zhang, J. Effect of film cooling structures on the cooling characteristics of plugs for two-dimensional (2-D) plug nozzle, Int J Therm Sci., 2023, 192, p 108444. doi: 10/gt33m3 CrossRefGoogle Scholar
Wang, H., Ji, H. and Lu, H. Experimental investigation on infrared radiation characteristics of two-dimensional convergent–divergent vectoring nozzle, J Thermophys Heat Transf., 2019, 33, pp 627–637. doi: 10/gtm2km CrossRefGoogle Scholar
Chen, J. and Ji, H.-H. Numerical simulation of the infrared radiation characteristics and infrared restraining effect of lower wall temperature for two-dimensional plug nozzle, Hangkong Dongli XuebaoJ Aerosp. Power., 2012, 27, pp 2429–2435.Google Scholar
Zhou, H.-C., Tan, H.-J. and Li, X.-P. Unique design method of subsonic inlet with complex cross-sectional shape, Hangkong Dongli XuebaoJ Aerosp. Power., 2009, 24, pp 1357–1363.Google Scholar
Hill, P.G., Philip, G. and Peterson, C.R. Mechanics and Thermodynamics of Propulsion. Boston, USA: Addison-Wesley, 1992.Google Scholar
Zheng, J. Research on Surface Cooling Characteristics of Plug Cone in 2-D Plug Vectoring Nozzle, 2016.Google Scholar
Silieti, M., Kassab, A.J. and Divo, E. Film cooling effectiveness: comparison of adiabatic and conjugate heat transfer CFD models, Int J Therm Sci., 2009, 48, pp 2237–2248. doi: 10/bjxvt6 CrossRefGoogle Scholar
Xu, H., Wang, J. and Wang, T. Numerical investigations of wake and shock wave effects on film cooling performance in a transonic turbine stage: Part 1 — Methodology development and qualification over stationary stators and rotors. In Volume 3B: Heat Transfer. San Antonio, TX, USA: American Society of Mechanical Engineers, p V03BT13A018, 2013. doi: 10.1115/GT2013-94544 CrossRefGoogle Scholar
Celik, I.B., Ghia, U. and Roache, P.J. Procedure for estimation and reporting of uncertainty due to discretization in CFD applications, J Fluids Eng., 2008, 130. doi: 10.1115/1.2960953 Google Scholar
Gao, X. Investigation on the Infrared Radiation and Radar Scattering Characteristics of Aircraft and Engine, Ph.D. dissertation of Northwestern Polytechnical University in 2016, Xi’an, China. 2016.Google Scholar