Hostname: page-component-848d4c4894-p2v8j Total loading time: 0.001 Render date: 2024-06-04T03:45:32.721Z Has data issue: false hasContentIssue false
  • English
  • Français

Experimental investigation of infrared signal characteristics in a micro-turbojet engine

Published online by Cambridge University Press:  05 April 2019

S. M. Choi ,
S. Kim ,
R. S. Myong  and
W. Kim
S. M. Choi*
Affiliation:
Chonbuk National University College of Engineering, Deokjin-Gu, Jeonju, Republic of Korea
S. Kim
Affiliation:
Chonbuk National University College of Engineering, Deokjin-Gu, Jeonju, Republic of Korea
R. S. Myong
Affiliation:
Chonbuk National University College of Engineering, Deokjin-Gu, Jeonju, Republic of Korea
W. Kim
Affiliation:
Chonbuk National University College of Engineering, Deokjin-Gu, Jeonju, Republic of Korea
*
*csman@jbnu.ac.kr
Get access Rights & Permissions [Opens in a new window]

Abstract

Infrared signal measurements from a micro-turbojet engine are conducted to understand the characteristics of the engine performance and the infrared signal by varying the exhaust nozzle configuration. A cone type nozzle and five rectangle type nozzles whose aspect ratios vary from one to five are used for this experimental work. As a result, it is confirmed that the thrust and the fuel consumption rate of the engine do not change greatly by varying the exhaust nozzle shape. In the case of the aspect ratio of 5, the specific fuel consumption of the engine is increased by about 3% compared to the reference cone nozzle, but the infrared signal can be reduced by up to 14%. As a result of measuring the temperature distribution of the plume gas, the correlation of infrared signal with plume gas temperature distribution can be understood. In the case of a cone shape, the distribution of plume gas formed to circular shape, and the high-temperature core region of plume gas continued to develop farther to the downstream. However, the temperature distribution was maintained in the rectangular shape as the aspect ratio increased, and the average temperature decreased sharply. As the aspect ratio increases, the plume spreads more widely.

Keywords

Micro-turbojet engineExhaust nozzleAspect ratioEngine performanceInfrared signalIrradiance
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1261 , March 2019 , pp. 340 - 355
Copyright
© Royal Aeronautical Society 2019 

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.)

Footnotes

‡

The original version of this article was published with an incorrect author name. A notice detailing this has been published and the error rectified in the online PDF and HMTL copies.

References

1. Ball, R.E. The Fundamentals of Aircraft Combat Survivability Analysis and Design, 2003. 2nd ed, AIAA Education Series, Reston, VA, USA.Google Scholar
2. Mahulikar, S.P., Sonawane, H.R. and Rao, G.A. Infrared signature studies of aerospace vehicles, Progress in Aerospace Sciences, 2007, 43, (7–8), pp 218–245.Google Scholar
3. Mahulikar, S.P., Rao, G.A. and Kolhe, P.S. Infrared signatures of low flying aircraft and their rear fuselage skin’s emissivity optimisation, J Aircr, 2006, 43, (1), pp 226–232.Google Scholar
4. Mahulikar, S.P., Rao, G.A., Sane, S.K. and Marathe, A.G. Aircraft plume infrared signature in nonafterburning mode, J Thermophysics and Heat Transfer, 2005, 19, (3), pp 413–415.Google Scholar
5. Thompson, J. and Birk, A. M. Design of an Infrared Signature Supressor for the Bell 205(UH-1H) Helicopter Part 1: Aerothermal Design, Proceedings of the 11th CASI Propulsion Symposium, 2010.Google Scholar
6. Decher, R. Infrared emission from turbofans with high aspect ratio nozzle, J Propulsion and Power, 2004, 20, (3), pp 527–532.Google Scholar
7. An, C.H., Kang, D.W., Baek, S.T., Myong, R.S., Kim, W.C. and Choi, S.M. Analysis of plume infrared signature of S-shaped nozzle configurations of aerial vehicle, Journal of Aircraft, 2016, 53, (6), pp 1768–1778.Google Scholar
8. Cfd-Fastran. Software Package, Ver. 2009, 2015, ESI Group, Paris.Google Scholar
9. Grosshandler, W.L. RADCAL: A Narrow-Band Model for Radiation Calculations in a Combustion Environment, National Technical Information Service, TN 1402, Alexandria, VA, 1993.Google Scholar
10. Walsh, P. P. and Fletcher, P. Gas Turbine Performance, 1998, Black Well Science Ltd.; pp 154–157.Google Scholar
11. Dix, J., Saddington, A.J., Knowles, K. and Richardson, M.A. Infra-red signature reduction study on a small-scale jet engine, Aeronautical J, 2005, 109, (1092), pp 83–88.Google Scholar