Application of Controlled Air By-Pass from the Turbofan Engine Compressor for Supersonic Passenger Plane

Aeronautical and Space-Rocket Engineering


Аuthors

Kalenskii S. M.*, Ezrokhi Y. A.**

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

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

Abstract

The authors consider the possibility of the bypass turbojet engine with controlled air by-pass from the compressor to the secondary duct for the supersonic passenger plane.

The turbojet engine should meet noise requirements at the takeoff mode. This is associated with the restriction of the jet efflux velocity from the jet nozzle, and the engine should be of rather high by-pass ratio.

Both high efficiency and bypass ratio reduction are required at the supersonic cruising mode.

The authors propose a variable cycle engine with controlled air bypass from the compressor to the secondary duct to make these controversial requirements consistent.

The most rational way is air bleeding behind the first stage of the high-pressure compressor. It saves energy consumption on the air bleed compression and improves its mixing arrangement.

Mathematical model of the said variable cycle engine is based on the mathematical model of the turbojet engine with flows mixing and common nozzle. The initial model is supplemented with the bleed air parameters computing block and a block for computing its mixing with the second circuit flow.

According to the widespread approach, the options of variable cycle engine were considered based on one and the same implemented gas generator of the fourth generation engine.

Computational esteems were conducted in two stages.

At the first stage, the initial bypass ratio effect on parameters of the conventional engine scheme and variable cycle engine with bypass were estimated.

Maximal takeoff mode was selected as a computational mode. The engine thrust values at the other modes of the flight cycle were being set proportional to the maximal takeoff mode thrust.

The compressor air bleed at the subsonic modes was 10% and 20% , and there was no bypass  at the supersonic modes.

At the second stage of computations, parameters comparison of the variable cycle engine and turbojet engine of the conventional scheme for their application as a part of similar flying vehicles has been executed (at the same air consumption).

The following results were obtained at the rated takeoff mode (with reduced noise level): the nozzle jet efflux velocity of the variable cycle engine will be  equal to the turbojet engine jet efflux velocity at the ~5.5% greater thrust; 2.5% less specific fuel consumption and 7.5% greater high-pressure compressor stability margin.

The variable cycle engine thrust will be the same as the one of the conventional turbojet engine at the prior to the turbine temperature increase by 20-25 K. Its specific fuel consumption herewith will reduce by ~0.5%.

Keywords:

air by-passing from the compressor, bypass turbfan engine, variable cycle engine, supersonic passenger plane

References

  1. Zrelov V.A. Otechestvennye gazoturbinnye dvigateli. Osnovnye parametry i konstruktivnye skhemy (Domestic gas turbine engines. Basic parameters and design schemes), Moscow, Mashinostroenie, 2005, 335 p.

  2. Sun Y., Smith H. Review and prospect of supersonic business jet design. Progress in Aerospace Sciences, 2017, vol. 90, pp. 12-38. DOI: 10.1016/j.paerosci.2016.12.003
  3. NASA Aeronautics. Strategic Implementation Plan. NP-2017-01-2352-HQ. 2017. URL: https://www.nasa.gov/sites/default/files/atoms/files/sip-2017-03-23-17-high.pdf
  4. Fomin V.M., Chirkashenko V.F., Volkov V.F., Kharitonov A.M. Teplofizika i aehromekhanika, 2011, vol.18, no. 4, pp. 525-541.
  5. Kovalenko V.V., Chernyshev S.M. Uchenye zapiski TSAGI, 2006, vol. XXXV, no. 3, pp. 53-62.
  6. Alendar' A.D., Lanshin A.I., Evstigneev A.A. et al. Vestnik Samarskogo universiteta. Aehrokosmicheskaya tekhnika, tekhnologii i mashinostroenie, 2023, vol. 22, no. 1, pp. 7-28. DOI: 10.18287/2541-7533-2023-22-1-7-28
  7. Chelebyan O.G., Strokin V.N., Shilova T.V. Aviatsionnye dvigateli, 2021, no. 3(12), pp. 55-62. DOI: 10.54349/26586061_2021_3_55
  8. Buonanno M. Conceptual design of a quiet supersonic technology airliner. Lockheed Martin Corporation. All Rights Reserved, 2019. URL: https://lbpw-ftp.larc.nasa.gov/aviation-2019/buonanno-lockheed-martin-conceptual-design-supersonic-a...
  9. From Concorde to New Supersonic Aircraft Projects. 2019. URL: https://academieairespace.com/wp-content/uploads/2019/06/AAE_D46_UK_WEB.pdf
  10. Gundry R. The Future of Supersonic Jets. Airport Noise Abatement Committee Meeting. 2019. URL: https://www.broward.org/Airport/Business/NoiseInformation/Documents/Hmmh_supersonic_presentation_sep...
  11. Mirzoyan A.A., Kokorev V.P. Dvigatel', 2011, no. 2(74), pp. 16-21.
  12. Yakurnova K.A., Alendar' A.D. Materialy Mezhdunarodnoi molodezhnoi nauchnoi konferentsii “XLVII Gagarinskie chteniya – 2021” (20-23 April 2021; Moscow), Moscow, Pero, 2021, pp. 202-203.
  13. Aerion unveils GE mill for AS2. Aviation International News. Ain publications. 2018. Vol. 49. No. 11. URL: https://www.ainonline.com/sites/default/files/full-issues/ain_1118.pdf
  14. Berton J.J., Huff D.L., Seidel J.A., Geiselhart K.A. Supersonic technology concept aeroplanes for environmental studies. AIAA SciTech Forum (06-10 January 2020; Orlando, Florida). DOI: 10.2514/6.2020-0263
  15. Berton J.J., Haller W.J., Senick P.F. et al. A Comparative Propulsion System Analysis for the High-Speed Civil Transport. NASA/TM-2005-213414. URL: https://www.researchgate.net/publication/287646257_A_Comparative_Propulsion_System_Analysis_for_the_...
  16. Vdoviak J.W., Thackeray M.J. Definition study for variable cycle engine testbed engine and associated test program. NASA CR-159459, 1978. URL: https://ntrs.nasa.gov/api/citations/19790004877/downloads/19790004877.pdf
  17. Vdoviak J.W., Knott P.R., Ebacker J.J. Aerodynamic/acoustic performance of YJ101/double bypass VCE with co annular plug nozzle. NASA CR-159869, 1981. URL: https://ntrs.nasa.gov/citations/19810009323
  18. Ezrokhi Yu.A. Mashinostroenie: entsiklopediya. T. IV-21. Samolety i vertolety. Kn. 3. Aviatsionnye dvigateli (Mechanical engineering: Encyclopedia. Vol. IV-21 Planes and helicopters. Book 3 Aircraft engines), Moscow, Mashinostroenie, 2010, pp. 341–353.
  19. Dvigateli aviatsionnye gasoturbinnye: metody i podprogrammy rascheta termodinamicheskikh parametrov vozdukha i productov sgoraniya uglevodorodnykh topliv. Rukovodyashiy tekhnicheskiy material aviatsionnoy teckhniki RTM 1677-83 (Aicraft gas turbine engines: methods and subroutines of air and hydrocarbon fuel combustion products thermodynamic parameters calculation. A guiding technical material of aviation technique, no. 1677-83), Moscow, TsIAM, 1983, 92 p.
  20. Filinov E.P., Kuz'michev V.S., Tkachenko A.Y., Ostapyuk Y.A. Determining required turbine cooling air flow rate at the conceptual design stage of gas turbine engine. Aerospace MAI Journal, 2021, vol. 28, no. 1, pp. 61-73. DOI: 10.34759/vst-2021-1-61-73.
  21. Gusmanova A.A., Ezrokhi Yu.A. Analysis of the possibility of creating different purpose aviation engines of the based engine core. Aerospace MAI Journal, 2023, vol. 30, no. 1, pp. 156-166. DOI: 10.34759/vst-2023-1-156-166

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