Studying the Swirler Blades Profile Impact on the Flow Structure and Parameters

Aeronautical and Space-Rocket Engineering


Аuthors

Wang F. *, Sharafutdinov R. R.**, Aleksandrov Y. B.***

Kazan National Research Technical University named after A.N. Tupolev, Kazan, Russia

*e-mail: VanF@stud.kai.ru
**e-mail: ramissharafutdinov15@gmail.com
***e-mail: Alexwischen@rambler.ru

Abstract

A comparative numerical study of the single-stage axial swirlers featuring three distinct vane profiles was conducted to minimize pressure losses and improve flow uniformity within the flame tube of a gas turbine combustion chamber. The studied profiles comprised straight vanes, circular-arc vanes, and rounded straight vanes. Detailed three-dimensional computational models of each swirler configuration were developed and simulated under isothermal conditions representative of a cold-flow rig test. A comprehensive analysis of the resultant downstream flow fields was performed, focusing on the vortex structure, velocity distribution, and associated hydraulic losses.
The primary objective consisted in systematically quantifying the vane profile geometry and the swirl parameter effect on the development of the central recirculation zone, its stability, and the consequent total pressure drop. Numerical solutions were obtained with a Reynolds-Averaged Navier–Stokes approach with an appropriate turbulence closure model, ensuring adequate resolution of the near-vane and core flow regions. The results conclusively demonstrate a direct and significant relationship between the swirl intensity, characterized by the swirl parameter, and key flow characteristics. As the swirl parameter increases, the axial length of the central recirculation zone contracts, while its radial extent expands substantially. This morphological change in the recirculation bubble is accompanied by a monotonic increase in the total pressure loss coefficient across all vane designs, underscoring the inherent trade-off between mixing enhancement and aerodynamic penalty.
A critical finding pertains to the flow mechanics within the vane passages. The inter-vane channels generate strongly converging (confusor-like) streams. Furthermore, flow separation from the vane surfaces, particularly pronounced in certain profiles, induces an additional effective contraction. This combined effect leads to localized acceleration, increased shear, and ultimately, higher irreversible losses. The study revealed as well a clear effect of the vane profile contour on the initial direction and spatial distribution of the exiting swirling jet, thereby affecting the subsequent interaction with the flame tube walls and the CRZ formation dynamics.
In conclusion, this integrated numerical study elucidates the complex interdependence among vane geometry, induced swirl strength, vortex topology, and hydraulic performance in a canonical swirler configuration. The findings provide fundamental insights and quantitative data linking design parameters to functional outcomes. Specifically, they offer practical guidance for optimizing swirler design to achieve a desired balance between strong, stable recirculation for flame anchoring and minimal pressure loss for overall engine efficiency, contributing to the advancement of combustion chamber performance and operational stability.

Keywords:

combustion chamber, flame tube head, vane swirler, blade profile, hydraulic losses

References

  1. Lefebvre AH. Gas turbine combustion. N.Y.: McGraw-Hill Book Co.; 1983. 531 p.
  2.  Chin JS. New Generation Aeroengine Combustor. Journal of Engineering Thermophysics. 2022;43(2):543-552. DOI: 10253-231X(2022)02-0543-10
  3.  Suo J, Liang H, Li  M, et al.  Design and Development System of Aeroengine Combustor. Aeronautics and Astronautics Science and Engineering. 2021;47(3). DOI: 10.13477/j.cnki.aeroengine.2021.03.005
  4.  Liu X. Study on low-emission combustion chamber Design and Premixed combustion characteristics. PhD thesis. Harbin Engineering University; 2018. DOI: 10.7666/d.D01411046
  5.  Fu J. Comparative test on performance of combustion chamber flame cylinder head. Aeroengine. 2023;49(04):128-133. DOI: 10.13477/j.cnki.aeroengine.2023.04.016
  6. Lanskii AM, Lukachev SV, Matveev SG. Research of raspylivaniya of fuel the pneumomassage sprayers. Trudy MAI. 2012(57). (In Russ.). URL: https://trudymai.ru/eng/published.php?ID=31093
  7. Isaev AI, Mairovich YuI, Safarbakov AM, et al. Influence of geometrical characteristics on the vortex structure in the pulse combustion chamber. Trudy MAI. 2016(88). (In Russ.). URL: https://trudymai.ru/eng/published.php?ID=70631 
  8. IsaevAI, Safarbakov AM, Mayrovich YuI. Optimization of control input to the vortex structure in the pulse combustion chamber. Reshetnevskie chteniya. 2014. p. 142-144.(In Russ.).
  9. Vainer LG, Nagorkin MN, Fomenko IE. Quality control of the mixture formation process in the combustion chamber of a gas turbine unit based on its information model. Vestnik TOGU. 2024(4):49-58. (In Russ.). DOI: 10.38161/1996-3440-2024-4-49-58
  10. Biryuk VV, Orlov MY, Zubrilin IA, et al. Specifying the dimensions of the reverse current area of a 3-D gas-turbine engine combustion chamber model using the ansys fluent software. Vestnik SamGAU. 2011(5):44-48. (In Russ.).
  11. Emmil' M.V. Swirling jets behind the blade swirlers in the free space and in the combustion chamber of the gas turbine engine. Izvestiya MGTU “MAMI”. 2014(1):86-90. (In Russ.).
  12.  Zhang Q, He X, Gong C, et al. Performance of swirling-flow single trapped vortex combustor under different swirler schemes. Journal of Aerospace Power. 2023(7):1773-1783. DOI: 10.13224/j.cnki.jasp.20210617
  13.  Zhu D, Tang H, Xie G. CFD Simulations of Radial Swirler. Dongfang electric review. 2014(112):55-60. DOI: 10.13661/j.cnki.issn1001-9006.2014.04.013
  14.  Zhang P, Wei T, Xi Y, et al. Influence of Swirler Blade Bending Angle on Swirl Characteristics. Technology Innovation and Application. 2023(7):76-80. DOI: 10.19981/j.CN23-1581/G3.2023.07.017
  15.  Ding M, Dong L, Ban R, et al. Numerical simulation study onflow field morphology influenced by bionic vanes of a dual-stage swirler. Journal of Propulsion Technology. 2024;46(4). DOI: 10.13675/j.cnki.tjjs.2401005
  16.  Xu X, Zegn W, Liu K, et al. Experimental testing and numerical calculation of flow field characteristics in a double stage axial swirl combustor. Journal of Aerospace Power. 2023;40(10). DOI: 10.13224/j.cnki.jasp.20230776 
  17.  Gu D, Shen C, Yang S, et al. Test of Concentric Staged Combustor Cold Flow Field Based on PIV. Aeroengine. 2023(1):76-80. DOI: 10.13477/j.cnki.aeroengine.2023.01.010
  18.  Wang Y, Xiao W, Wang Z, et al. Numerical Simulation and Test Verification of the Influence of Airflow Splits on the Flow Field Characteristics in Dual-axial Swirlers. Aeroengine. 2022(1):26-32. DOI: 10.13477/j.cnki.aeroengine.2022.01.005
  19.  Liu K, Xu R, Cao J, et al. Influence of swirler and flame tube matching on combustion performance. Journal of Aerospace Power. 2024;40(12). DOI: 10.13224/j.cnki.jasp.20240614
  20. Nguyen TD, Alexandrov YuB, Mingazov BG. Influence of the fairing shape on the uniformity of the velocity profile in front of the swirler blades. Materialy nauchno-tekhnicheskoi konferentsii “Klimovskie chteniya – 2020: perspektivnye napravleniya razvitiya aviadvigatelestroeniya”(October 16, 2020; Saint Petersburg ). St. Petersburg: Skifiya-print; 2020. p. 93-101.
  21. Aleksandrov YB., Nguyen TD., Mingazov BG., et al. Swirler vanes installation angle impact on flow mixing efficiency behind the flame tube head of gas turbine engine combustion chamber. Aerospace MAI Journal. 2021;28(3):146-158. (In Russ.).DOI: 10.34759/vst-2021-3-146-158

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