A Conceptual Design Technique for the Civil Aviation Aircraft Gas Turbine Engines Combustion chambers

Aeronautical and Space-Rocket Engineering


Аuthors

Orlova E. V.*, Orlov M. Y.**

Samara National Research University named after Academician S.P. Korolev, Moskovskoe shosse, 34, Samara, Russia

*e-mail: adler_e_v@mail.ru
**e-mail: adler65@mail.ru

Abstract

The article adduces description of the developed technique for the layout shaping of the combustion chambers for aircraft gas turbine engines of the latest generations intended for civil aviation. With a view to the political situation, it is important for Russia to ensure the development of domestic civil aviation aircraft and their engines. The solution to this problem is associated with import substitution. Currently, the gas turbine engine combustion chamber is the most complex engine element in terms of design and refinement. It is stipulated by the lack of reliable mathematical models of the working process due to the presence of combustion and turbulent gas flows, the constant growth of cycle parameters, as well as the stricter requirements for the combustion chamber, which it must meet. When creating a combustion chamber, its layout forming at the early design stages plays an important role. It is impossible to compute the working process and characteristics of the combustion chamber in the absence of its geometry. The combustion chamber layout is its geometric shape with the dimensions of the flow part. Subsequently, based on the combustion chamber layout, a mathematical model of the workflow and computations in SAE systems are being performed to evaluate the characteristics of the product. However, the currently available techniques allow creation of the combustion chamber shapes only for engines of the third, less often fourth generations. Thus, the developed technique is adapted to the combustion chambers of modern civil aviation engines. The technique that has passed the test of time and was employed by the “ODK-Kuznetsov” Public Joint Stock Company was selected as the basic one. This technique includes 118 formulas that make up the computational algorithm for the flow part of the NK-8 engine combustion chamber. Within the framework of this work the data was accumulated and analysis of combustion chambers of both narrow- and wide-body aircraft was performed. Then, the numerical values of the empirical coefficients were replaced in the computational formulas of the basic methodology. The combustion chamber images constructing with various combustion technologies, such as TAPS, TALON, etc., allowed revealing that each combustion technology has its own mathematical description. Thus, it is important to select the right prototype of the projected combustion chamber in the beginning of the conceptual design. For this purpose, a block was added to the developed technique. In this block, based on the requirements for the designed engine, the input and output parameters of the combustion chamber (the degree of pressure increase behind the compressor and the temperature of the gas at the turbine inlet) are evaluated. Further, a prototype with a specific combustion technology is being selected. The developed methodology includes as well a block, in which total pressure losses are being computed based on the formed shape. There is also a possibility to apply the technique in thermo-gas-dynamic engine computing programs, which allows increasing their efficiency, as well as providing an opportunity to refine the power plant mass.

Keywords:

layout construction of the gas turbine engine combustion chambers, combustion chambers conceptual design technique, combustion technologies selection

References

  1. Inozemtsev AA, Nikhamkin MA, Sandratskii VL. Fundamentals of the design of aircraft engines and power plants. Perm: Aviadvigatel'; 2006. 1204 p. (In Russ).
  2.  Orlov MYu, Zrelov VA, Orlova EV. Statistic data application for narrow-body aircraft engines combustion chambers preliminary design. Aerospace MAI Journal. 2022;29(4):151-160. (In Russ.). DOI: 10.34759/vst-2022-4-151-160.
  3.  Orlov MYu, Orlova EV. Analysis of statistical data for conceptualization of combustion chambers of aircraft gas turbine engines for wide-body aircraft. Vestnik RGATA im. P.A. Solov'eva. 2022(2):32-38. (In Russ.).
  4.  Babkin VI, Tskhovrebrov MM, Solonin VI, et al. The development of aviation GTE and the creation of unique technologies. Dvigatel'. 2013(2):2-7. (In Russ.).
  5.  Lefebvre A. Gas Turbine Engine Combustion. McGraw-Hill Inc., US; 1983. 531 p. 
  6.  Baklanov AV. Stepwise gas turbine engine combustion chamber development in conditions of air velocity forcing at compressor outlet. Aerospace MAI Journal. 2017;24(3):13-22. (In Russ.).
  7.  Aleksandrov YuB, Nguen TD, Mingazov BG. Design and development of combustion chambers for gas turbine engines based on calculations of various levels of complexity. Vestnik of Samara University. Aerospace and mechanical engineering. 2021;20(3):7-23. (In Russ.). DOI: 10.18287/2541-7533-2021-20-3-7-23
  8.  Moreno-Pacheco LA, Sánchez-López F, Barbosa-Saldaña JG, et al. Design and Numerical Analysis of an Annular Combustion Chamber. Fluids. 2024;9(7):161. DOI: 10.3390/fluids9070161
  9.  Jagadish V., Anandarao G., Maddaiah K.C., et al. Design and Analysis of Gas Turbine Combustion Chamber. AIP Conference Proceedings. 2023;2492:20031. DOI:10.1063/5.0113361
  10.  Mark CP, Selwyn A. Design and Analysis of Annular Combustion Chamber of a Low Bypass Turbofan Engine in a Jet Trainer Aircraft. Propulsion and Power Research. 2016;5(2):97–107. DOI: 10.1016/j.jppr.2016.04.001
  11.  Balijepalli R., Dasore A. Design and Optimisation of Annulus Combustion Chamber of Gas Turbine Engine: An Analytical and Numerical Approach. In book: Verma P., Samuel O.D., Verma T.N., et al. (eds) Advancement in Materials, Manufacturing and Energy Engineering. Vol. II. Lecture Notes in Mechanical Engineering. Springer, Singapore; 2022. p. 553-567. DOI: 10.1007/978-981-16-8341-1_47
  12.  Zrelov VA. Domestic aviation gas turbine engines. Basic parameters and design schemes. Moscow: Mashinostroenie; 2005. 336 p. (In Russ.).
  13.  Sorokin L.I. Foreign aircraft engines and gas turbine installations (based on materials from foreign publications). Handbook. Moscow: TsIAM; 2010. 413 p. (In Russ.).
  14.  Roux E. Turbofan and Turbojet Engines. Database Handbook. Elodie ROUX; 2007. 595 p.
  15.  Pchelkin YuM. Combustion chambers of gas turbine engines. 3rd ed. Moscow: Mashinostroenie; 1984. 280 p. (In Russ.).
  16.   Gritsenko EA, Danil'chenko VP, Lukachev SV, et al. Some design issues of aviation gas turbine engines. Samara: SNTs RAN; 2002. 526 p. (In Russ.).
  17.   Mingazov BG, Yavkin VB. Automated calculation and design of combustion chambers of gas turbine engines. Kazan: KGTU; 2002. 54 p. (In Russ.).
  18.  Yize L, Xiaoxiao S, Sethi V, et al. Review of modern low emissions combustion technologies for aero gas turbine engines. Progress in Aerospace Sciences. 2017;94:12-45. DOI: 10.1016/j.paerosci.2017.08.001
  19.  Tkachenko AYu, Kuz'michev VS, Filinov EP, et al. Aircraft target purpose impact on working process optimal parameters and power plant configuration. Aerospace MAI Journal. 2020;27(2):112-122. (In Russ.). DOI: 10.34759/vst-2020-2-112-122
  20.  Kuz'michev VS, Filinov EP, Ostapyuk YaA. Comparative fidelity analysis of turbofan engines masses mathematical models. Trudy MAI. 2018(100). (In Russ.). URL: https://trudymai.ru/published.php?ID=93362

mai.ru — informational site of MAI

Copyright © 1994-2025 by MAI