Accounting for the effect of the border layer at the inlet to the fans while integrating the distributed power plant and a flying vehicle

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


Аuthors

Ezrokhi Y. A.*, Kalenskii S. M.**, Morzeeva T. A.**, Khoreva E. A.**

Central Institute of Aviation Motors named after P.I. Baranov, CIAM, 2, Aviamotornaya str., Moscow, 111116, Russia

*e-mail: yaezrokhi@ciam.ru
**e-mail: 30105@ciam.ru

Abstract

The article presents the analysis of a distributed power plant concept for perspective long haul passenger aircraft, which is intended for ensuring more deep integration of a power plant and a flying vehicle, as well as enhancing its fuel efficiency.

While employing an aircraft engine of such kind, separate modules of a power plant may be installed both in the engine nacelle and inside an airplane fuselage, made according to a “flying wing” scheme.

A portion of a boundary layer, formed at the surface of an aircraft, gets into the inlet plane of fan modules, located at the top surface of the fuselage.

The variant of a submerged engine inside an aircraft assumes the presence of a rather long curvilinear intake channel, in which local separations and vortexes inevitably occur. It leads to additional losses of full pressure at the engine inlet.

The article considers separately the effect of two main factors on the engine thrust, namely, the drop of overall level of the total pressure at the engine inlet and its non-uniformity.

To evaluate the effect of the above said components, the results of preliminary work out of the distributed power plant parameters, obtained at CIAM, named for Baranov, in the activities progress on the engines' schemes of new types, were applied.

Calculations were performed employing the first level model of an aircraft gas turbine engine.

Parametrical studies performed using the developed technique allowed select an optimal degree of double-flowness on specific fuel consumption at course speed, and the degree of pressure increase in the fan. The fan modules' and main engine components dimensionality was redetermined with account for various losses levels at the inlet.

The effect of engine parameters changing on the its mass estimation value was performed with the developed modular technique, based on the idea of impeller machine mass proportionality to compression specific work and corrected specific air consumption. The modular technique coefficients characterizing the weight fraction of the turbojet modules were determined based on estimations obtained for detailed element-by-element mathematical model of mass, in the activities progress on the engines' schemes of new types, at CIAM, named for Baranov.

The obtained results of the parametrical studies make it clear that on deterioration of the factor of total pressure preservation at the inlet by 2%, minimum specific fuel consumption at a cruising mode would be achieved in the distributed power plant with double-flowness reduced by 3%, and the total pressure increase degree in the fan reduced by 0.6%. At the same time specific fuel consumption increases on 6-7 % of percent. The specific fuel consumption herewith is increases by 6-7%.

The power plant weight, without account for the weight of the remote fan modules transmission drive may increase by approximately 4-5 %.

Analysis of the effects associated with the presence of non-uniform total pressure field, resulting in its averaged level reduction at the fan inlet, revealed that the effect of non-uniformity presence itself might be of 15 to 30% of the total effect on the engine thrust. It should be accounted for selection of the distributed power plant shape of the configuration under consideration.

Keywords:

turbojet bypass engine, perspective long haul airplane, gas-generator of a turbojet bypass engine, fan module, turbojet bypass engine design, distributed power plant

References

  1. Ezrokhi Yu.A., Kalenskii S.M., Morzeeva T.A., Ryabov P.A., Isyanov A.M. Osnovnye rezul'taty nauchno-tekhnicheskoi deyatel'nosti TsIAM-2016, Moscow, TsIAM, 2016, pp. 51-54.

  2. Tskhovrebov M.M., Khudyakov E.I., Polev A.S. Osnovnye rezul'taty nauchno-tekhnicheskoi deyatel'nosti TsIAM (2010-2014), Moscow, TsIAM, 2015, pp. 56-65.

  3. Kalenskii S.M., Morzeeva T.A., Ezrokhi Yu.A. Vserossiiskaya nauchno-tekhnicheskaya konferentsiya “Aviadvigateli XXI veka” (24-27 November 2015). Sbornik statei, Moscow, TsIAM, 2015, pp. 59-61.

  4. Karasev D.A., Arutyunov A.G., Zagordan A.A. Vestnik Moskovskogo aviatsionnogo instituta, 2015, vol. 22, no. 1, pp. 132-139.

  5. Skibin V.A., Solonin V.I., Palkin V.A. Raboty vedushchikh aviadvigatelestroitel'nykh kompanii v obespechenie sozdaniya perspektivnykh aviatsionnykh dvigatelei (Works of leading aircraft engine companies to ensure creation of advanced aircraft engines), Moscow, TsIAM, 2010, 672 p.

  6. Ezrokhi Yu.A., Kalenskii S.M., Morzeeva T.A., Kizeev I.S. Vestnik Moskovskogo aviatsionnogo instituta, 2017, vol. 24, no. 2, pp. 31-41.

  7. Torg M.T., Scott M.J., Haller W.J., Handschuh R.F. Engine Conceptual Design Studies for a Hybrid Wing Body Aircraft. Prepared for the Turbo Expo 2009 sponsored by the American Society of Mechanical Engineers, Orlando, Florida, June 8-12, 2009. NASA/TM-2009-215680, 2009, 9 p. URL: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20090042817.pdf

  8. Greitzer E. M. Some aerodynamic problems of aircraft engines – fifty years after. Gas Turbine Laboratory, Massachusetts Institute of Technology Cambridge, MA 02139, USA Proceedings of GT2007 ASME Turbo Expo 2007: Power for Land, Sea and Air May 14-17, 2007, Montreal, Canada. GT2007-28364, 17 p.

  9. Plas A.P., Sargeant M.A., Madani V., Crichton D., Greitzer E.M., Hynes T.P., Hall C.A. Performance of a Boundary Layer Ingesting (BLI) Propulsion System. 45th AIAA Aerospace Sciences Meeting and Exhibit 8-11 January 2007, Reno, Nevada Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, MA, Engineering Department, University of Cambridge, Cambridge, UK, 21 p.

  10. Demenchenok V.P., Druzhinin L.N., Parkhomov A.L., Sosunov V.A., Tskhovrebov M.M., Shlyakhtenko S.M., El'perina A.S. Teoriya dvukhkonturnykh turboreaktiv-nykh dvigatelei (Theory of turbojet engines), Moscow, Mashinostroenie, 1979, 432 p.

  11. Goryunov A.I., Goryunov I.M. Vestnik UGATU, 2010, no. 3, pp. 57-61.

  12. Ezrokhi Yu.A., Kalenskii S.M., Kizeev I.S. Vestnik Moskovskogo aviatsionnogo instituta, 2017, vol. 24, no. 1, pp. 26-38.

  13. Ezrokhi Yu.A., Khoreva E.A., Kizeev I.S. Vestnik Moskovskogo aviatsionnogo instituta, 2017, vol. 24, no. 4, pp. 46-51.

  14. Pudovkin I.Yu., Kizeev I.S., Ezrokhi Yu.A. Svidetel'stvo o gosudarstvennoi registratsii program No 2596413, 10.08.2016.

  15. Longley J.P., Greitzer E.M. Inlet Distortion Effects in Aircraft Propulsion System Integration. Fundamentals and Special Problems of Synthetic Aperture Radar (SAR). AGARD Lecture Series, 1992. Paper 92-AD-20694, 16 р.

  16. Kurzke J. Effects of Inlet Flow Distortion on the Performance of Aircraft Gas Turbines. Journal of Engineering for Gas Turbines and Power, 2008, vol. 130, no. 4, pp. 117-125. DOI: 10.1115/1.2901190

  17. Ezrokhi Yu.A., Khoreva E.A. Aerokosmicheskii nauchnyi zhurnal, 2017, vol. 3, no. 3, http://aerospace.elpub.ru/jour/issue/view/19 DOI: http://dx.doi.org/10.24108/aersp.0317.0000064

  18. Khoreva E.A., Ezrokhi Yu.A. Aerokosmicheskii nauchnyi zhurnal, 2017, vol. 3, no. 1, http://aerospace.elpub.ru/jour/issue/view/15 DOI: http://dx.doi.org/10.24108/rdopt.0117.0000059

  19. Abramovich G.N. Prikladnaya gazovaya dinamika (Applied gas speaker), Moscow, Nauka, 1991, vol. 1− 600 p.

  20. Krasnov S.E. Tekhnika vozdushnogo flota, 2016, no. 2-3 – 86 p.

mai.ru — informational site of MAI

Copyright © 1994-2024 by MAI