Journal of the Korean Society for Aeronautical & Space Sciences (한국항공우주학회지)

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Computational and Experimental Investigation of Thermal Flow Field of Micro Turbojet Engine with Various Nozzle Configurations

노즐 형상 변경에 따른 마이크로 터보제트 엔진의 열유동장에 관한 전산해석 및 실험적 연구

  • Lee, Hyun-Jin (Department of Aerospace and Software Engineering and Research Center for Aircraft Parts Technology, Gyeongsang National University) ;
  • Lee, Ji-Hyun (Department of Aerospace and Software Engineering and Research Center for Aircraft Parts Technology, Gyeongsang National University) ;
  • Myong, Rho-Shin (Department of Aerospace and Software Engineering and Research Center for Aircraft Parts Technology, Gyeongsang National University) ;
  • Kim, Sun-Mi (Chonbuk National University) ;
  • Choi, Sung-Man (Chonbuk National University) ;
  • Kim, Won-Cheol (Agency for Defense Development)
  • Received : 2017.06.01
  • Accepted : 2018.01.04
  • Published : 2018.02.01
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Abstract

Numerical simulation and experimental study on the thermal flow field of the micro turbojet engine have been carried out for the purpose of developing infrared reduction technology for aircraft. A circular basic nozzle and five rectangular nozzles with different aspect ratio were considered. The conditions for CFD analysis were derived from the analysis of the engine performance. The temperature distribution of the nozzle plume was measured using a temperature sensing system. The thrust of the rectangular nozzle with the aspect ratio 5 was reduced about 1.8% compared to the circular nozzle, and the thrust decreased with increasing the aspect ratio of the nozzle. In the case of thermal flow field, it was observed that, as the aspect ratio increases, the exhaust plume in the experiment was formed wider than in the CFD analysis.

항공기 추진기관의 적외선 저감기술을 개발할 목적으로 축소모델인 마이크로 터보제트 엔진의 열유동장에 대한 전산해석 및 실험적 연구를 수행하였다. 이를 위해 원형의 기본노즐과 세장비에 따른 5개의 사각형 형상변형 노즐을 고려하였다. 먼저 엔진 성능 분석을 통하여 전산해석을 위한 계산조건을 도출하였다. 또한 전동식 온도 측정 장치를 이용하여 노즐의 정 후방 특정 위치별 열유동장 분포를 측정하였다. 세장비가 5인 사각 노즐의 추력손실은 원형노즐 대비 약 1.8%이었으며, 노즐 출구의 세장비가 커짐에 따라 추력은 대체적으로 감소하는 경향을 확인하였다. 열유동장의 경우, 세장비가 커짐에 따라 해석에 비해 실험에서 배기 플룸이 더 넓게 형성되었다.

Keywords

References

  1. Rao, G. A., and Mahulikar, S. P., "Effect of Atmospheric Transmission and Radiance on Aircraft Infrared Signatures," Journal of Aircraft, Vol. 42, No. 4, 2005, pp.1046-1054. https://doi.org/10.2514/1.7515
  2. Mahulikar, S. P., Rao, G. A., and Kolhe, P. S., "Infrared Signatures of Low-Flying Aircraft and Their Rear Fuselage Skin's Emissivity Optimization," Journal of Aircraft, Vol. 43, No. 1, 2006, pp.226-232. https://doi.org/10.2514/1.15365
  3. Kim, J. Y., Chun, S. H., Myong, R. S., and Kim, W. C., "Computational Investigation of the Effect of Various Flight Conditions on Plume Infrared Signature," Journal of the Korean Society for Aeronautical and Space Sciences, Vol. 41, No. 3, 2013, pp.185-193. https://doi.org/10.5139/JKSAS.2013.41.3.185
  4. Kang, D. W., Kim, J. Y., Myong, R. S., and Kim, W. C., "Computational Investigation of the Effect of UAV Engine Nozzle Configuration on Infrared Signature," Journal of the Korean Society for Aeronautical and Space Sciences, Vol. 41, No. 10, 2013, pp.779-787. https://doi.org/10.5139/JKSAS.2013.41.10.779
  5. Kim, M. J., Kang, D. W., Myong, R. S., and Kim, W. C., "Investigation of the Effects of UAV Nozzle Configurations on Aircraft Lock-on Range," Journal of the Korean Society for Aeronautical and Space Sciences, Vol. 43, No. 3, 2015, pp.204-212. https://doi.org/10.5139/JKSAS.2015.43.3.204
  6. Park, G. S., Kim, S. M., Choi, S. M., Myong, R. S., and Kim, W. C., "Experimental Study of a Micro Turbo Jet Engine Performance and IR Signal with Nozzle Configuration," Journal of the Korean Society of Propulsion Engineers, Vol. 20, No. 5, 2016, pp.1-8. https://doi.org/10.6108/KSPE.2016.20.5.001
  7. Gu, B. C., Baek, S. W., Jegal, H. W., Choi, S. M., and Kim, W. C., "Measurement and Validation of Infrared Signature from Exhaust Plume of a Micro-Turbo Engine," Journal of the Korean Society for Aeronautical and Space Sciences, Vol. 44, No. 12, 2016, pp.1054-1061. https://doi.org/10.5139/JKSAS.2016.44.12.1054
  8. Chun, S. H., Yang, Y. R., Moon, H., Myong, R. S., and Kim, W. C., "Computational Investigation of Nozzle Flowfields at Various Flight Conditions for Aircraft Infrared Signature Analysis," Journal of the Korean Society for Aeronautical and Space Sciences, Vol. 16, No. 13, 2011, pp.15-21.
  9. Moon, H., Yang, Y. R., Chun, S. H., Choi, S. M., Myong, R. S., and Kim, W. C., "Computation of Flowfield and Infrared Signature in Aircraft Exhaust System for IR Reduction Design," Journal of the Korean Society for Aeronautical and Space Sciences, Vol. 39, No. 7, 2011, pp.652-659. https://doi.org/10.5139/JKSAS.2011.39.7.652
  10. Kang, D. W., Kim, I. D., Myong, R. S., and Kim, W. C., "Investigation of Aircraft Plume IR Signature for Various Nozzle Configurations and Atmospheric Conditions," Journal of the Korean Society for Aeronautical and Space Sciences, Vol. 42, No. 1, 2014, pp.10-19. https://doi.org/10.5139/JKSAS.2014.42.1.10
  11. An, S. Y., Kim, W. C., and Oh, S. H., "A Study on the Effect of Engine Nozzle Configuration on the Plume IR Signature," Journal of the Korean Society for Aeronautical and Space Sciences, Vol. 40, No. 8, 2012, pp.688-694. https://doi.org/10.5139/JKSAS.2012.40.8.688
  12. An, C. H., Kang, D. W., Baek, S. T., Myong, R. S., Kim, W. C., and Choi, S. M., "Analysis of Plume Infrared Signatures of S-Shaped Nozzle Configurations of Aerial Vehicle," Journal of Aircraft, Vol. 53, No. 6, 2016, pp.1768-1778. https://doi.org/10.2514/1.C033685
  13. Banken, G. J., Cornette, W. M., and Gleason, K. M., "Investigation of Infrared Characteristics of Three Generic Nozzle Concepts," AIAA/SAE/ASME 16th Joint Propulsion Conference, 1980.