Estimation of the aerodynamic characteristics of a stepped nacelle for the aircraft powerplant

Authors

DOI:

https://doi.org/10.15587/1729-4061.2019.183403

Keywords:

stepped nacelle, aerodynamic drag, lift force, gas turbine engine, turbofan unit

Abstract

The purpose of this work is to estimate the aerodynamic characteristics of the stepped nacelle of a gas turbine engine with a turbofan unit. The research was based on the method of model physical experiment. The wind tunnel applied for the study was provided with the necessary equipment, which includes various nozzles of static and dynamic pressure with coordinate devices, etc. For the experimental study, we built the models of nacelles for an aviation power plant with front location of the fan module and with the rear arrangement of a turbofan unit. We have experimentally investigated the aerodynamic characteristics of the stepped nacelle for a gas turbine engine with a turbofan unit.

The results of this study demonstrated a possibility to decrease the aerodynamic drag of the stepped nacelle for an engine with a turbofan unit compared to the nacelle of a turbojet double-pass engine with the front arrangement of the fan. In the range of angles of attack α=0...20° the value of aerodynamic drag of the stepped nacelle for a gas turbine engine with a turbofan unit decreases by 49...55 %.

The obtained results showed that the coefficient of lifting power of the stepped nacelle for a gas turbine engine with a turbofan unit increases by 24...64 %. The coefficient of aerodynamic drag is lower by 18...28 % compared with the aerodynamic drag coefficient of a cylindrical nacelle for a double-pass turbojet engine in the range of angles of attack α=2...20°. Our findings indicate the prospects of using engines with a turbofan unit. The structural feature of the stepped nacelle would reduce the loss of efficient engine thrust by decreasing aerodynamic drag almost by two times and could increase fuel efficiency of the engine

Author Biographies

Yuriy Yu. Tereshchenko, National Aviation University Kosmonavta Komarova ave., 1, Kyiv, Ukraine, 03058

PhD

Department of Aviation Engine

Yuriy M. Tereshchenko, National Aviation University Kosmonavta Komarova ave., 1, Kyiv, Ukraine, 03058

Doctor of Technical Sciences, Professor

Department of Aviation Engine

 

Alexander Sklyarov, State Aviation Research Institute Andriushchenka str., 6v, Kyiv, Ukraine, 01135

PhD, Senior Researcher

Research Department No. 22

Ekaterina Doroshenko, National Aviation University Kosmonavta Komarova ave., 1, Kyiv, Ukraine, 03058

Doctor of Technical Sciences, Associate Professor

Department of Aviation Engine

Pavlo Humeniuk, National Aviation University Kosmonavta Komarova ave., 1, Kyiv, Ukraine, 03058

Postgraduate student

Department of Aviation Engine

References

  1. Chekalova, N. I. (2015). Methods of calculation of engine gondolas and landing gears resistance. Civil Aviation High Technologies, 211, 136–137.
  2. Malouin, B., Gariépy, M., Trépanier, J.-Y., Laurendeau, É. (2015). Internal Drag Evaluation for a Through-Flow Nacelle Using a Far-Field Approach. Journal of Aircraft, 52 (6), 1847–1857. doi: https://doi.org/10.2514/1.c033093
  3. Zhang, Y., Chen, H., Fu, S., Zhang, M., Zhang, M. (2015). Drag prediction method of powered-on civil aircraft based on thrust drag bookkeeping. Chinese Journal of Aeronautics, 28 (4), 1023–1033. doi: https://doi.org/10.1016/j.cja.2015.06.015
  4. Robinson, M., MacManus, D. G., Sheaf, C. (2018). Aspects of aero-engine nacelle drag. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 233 (5), 1667–1682. doi: https://doi.org/10.1177/0954410018765574
  5. Trapp, L. G., Argentieri, H. G. (2010). Evaluation of nacelle drag using computational fluid dynamics. Journal of Aerospace Technology and Management, 2 (2), 145–153. doi: https://doi.org/10.5028/jatm.2010.02026410
  6. Li, J., Gao, Z., Huang, J., Zhao, K. (2013). Aerodynamic design optimization of nacelle/pylon position on an aircraft. Chinese Journal of Aeronautics, 26 (4), 850–857. doi: https://doi.org/10.1016/j.cja.2013.04.052
  7. Sasaki, D., Nakahashi, K. (2011). Aerodynamic Optimization of an Over-the-Wing-Nacelle-Mount Configuration. Modelling and Simulation in Engineering, 2011, 1–13. doi: https://doi.org/10.1155/2011/293078
  8. Peters, A., Spakovszky, Z. S., Lord, W. K., Rose, B. (2014). Ultra-Short Nacelles for Low Fan Pressure Ratio Propulsors. Volume 1A: Aircraft Engine; Fans and Blowers. doi: https://doi.org/10.1115/gt2014-26369
  9. Robinson, M. H., MacManus, D. G., Richards, K., Sheaf, C. (2017). Short and slim nacelle design for ultra-high BPR engines. 55th AIAA Aerospace Sciences Meeting. doi: https://doi.org/10.2514/6.2017-0707
  10. Savelyev, A., Zlenko, N., Matyash, E., Mikhaylov, S., Shenkin, A. (2016). Optimal design and installation of ultra high bypass ratio turbofan nacelle. AIP Conference Proceedings, 1770. doi: https://doi.org/10.1063/1.4964065
  11. Tereshchenko, Y. Y., Tereshchenko, Y. M., Doroshenko, K. V., Usenko, V. Y. (2018). Profile resistance of a gas-turbine engine nacelle with a turbofan attachment. Problems of friction and wear, 4, 64–73.
  12. Yugov, O. K., Selivanov, O. D. (1980). Soglasovanie harakteristik samoleta i dvigatelya. Moscow: Mashinostroenie, 200.

Downloads

Published

2019-11-12

How to Cite

Tereshchenko, Y. Y., Tereshchenko, Y. M., Sklyarov, A., Doroshenko, E., & Humeniuk, P. (2019). Estimation of the aerodynamic characteristics of a stepped nacelle for the aircraft powerplant. Eastern-European Journal of Enterprise Technologies, 6(7 (102), 27–31. https://doi.org/10.15587/1729-4061.2019.183403

Issue

Vol. 6 No. 7 (102) (2019): Applied mechanics

Section

Applied mechanics

License

Copyright (c) 2019 Yuriy Yu. Tereshchenko, Yuriy M. Tereshchenko, Alexander Sklyarov, Ekaterina Doroshenko, Pavlo Humeniuk

Creative Commons License

This work is licensed under a Creative Commons Attribution 4.0 International License.

The consolidation and conditions for the transfer of copyright (identification of authorship) is carried out in the License Agreement. In particular, the authors reserve the right to the authorship of their manuscript and transfer the first publication of this work to the journal under the terms of the Creative Commons CC BY license. At the same time, they have the right to conclude on their own additional agreements concerning the non-exclusive distribution of the work in the form in which it was published by this journal, but provided that the link to the first publication of the article in this journal is preserved.

A license agreement is a document in which the author warrants that he/she owns all copyright for the work (manuscript, article, etc.).
The authors, signing the License Agreement with TECHNOLOGY CENTER PC, have all rights to the further use of their work, provided that they link to our edition in which the work was published.
According to the terms of the License Agreement, the Publisher TECHNOLOGY CENTER PC does not take away your copyrights and receives permission from the authors to use and dissemination of the publication through the world's scientific resources (own electronic resources, scientometric databases, repositories, libraries, etc.).
In the absence of a signed License Agreement or in the absence of this agreement of identifiers allowing to identify the identity of the author, the editors have no right to work with the manuscript.
It is important to remember that there is another type of agreement between authors and publishers – when copyright is transferred from the authors to the publisher. In this case, the authors lose ownership of their work and may not use it in any way.