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Xiong Moyou, Le Jialing, Huang Yuan, Song Wenyan, Yang Shunhua, Zheng Zhonghua. Experimental and simulation study of aeroengine combustor based on CARS technology and UFPV approach[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(5): 15-23. DOI: 10.11729/syltlx20170090
Citation: Xiong Moyou, Le Jialing, Huang Yuan, Song Wenyan, Yang Shunhua, Zheng Zhonghua. Experimental and simulation study of aeroengine combustor based on CARS technology and UFPV approach[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(5): 15-23. DOI: 10.11729/syltlx20170090
shu

Experimental and simulation study of aeroengine combustor based on CARS technology and UFPV approach

  • 1.

    School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

  • 2.

    Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Funds: 

Supported by NSFC 91641205

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  • Author Bio:

    Xiong Moyou(1987-), male, born in Qijiang county, Chongqing city, doctoral candidate.Engaged in combustion and flow in aero-engine research.Address:School of Power and Energy, Northwestern Polytechnical University (710072).E-mail:xmy19870102@126.com

  • Corresponding author:

    Xiong Moyou, E-mail:xmy19870102@126.com

  • Received Date: July 04, 2017
  • Revised Date: September 27, 2017
    Graphical Abstract
    • Abstract
  • Based on the Unsteady Reynolds Averaged Navier Stokes URANS) method, a three-dimensional two-phase turbulent combustion numerical software for aeroengine combustor has been developed. The physical and chemical processes taking place in the liquid fuel are simulated completely, including liquid film formation, breakup, evaporation and combustion. LISA and KH-RT are used as the primary and second atomization model respectively, and also the standard evaporation model is used to simulate the evaporation process. Besides, detailed chemical mechanism of kerosene is used for reaction kinetics, and the Unsteady Flamelet/Progress Variable (UFPV) approach in which the unstable combustion characteristics of the flame could be simulated is used as the combustion model. The temperature and species of the flow field and the diameter of fuel droplets in the aeroengine combustor are obtained. At the same time, the Coherent Anti-stokes Raman Scattering (CARS) technology is used to measure the temperature in the primary zone of the aeroengine combustor. Then the temperature of the simulation is compared with that measured by CARS technology, and the calculation error of numerical results is less than 7.3%. The studies have shown that the numerical method in this paper and UFPV approach can simulate the two-phase turbulent combustion process appropriately in the aeroengine combustor.
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    • References (20)
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