Experimental study on characteristics of cold time-averaged flow field in a five-nozzle can combustor

被引：0
|
作者：
Jin M. [1 ]
Lu Y. [1 ]
Liu Z. [1 ]
Ji Y. [1 ]
Ge B. [1 ]
Zang S. [1 ]
机构：
[1] School of Mechanical Engineering, Shanghai Jiaotong University, Shanghai
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2024年 / 45卷 / 05期
关键词：
Five-nozzle combustor; Inlet velocity; PIV; Recirculation zone; Swirl intensity;
D O I：
10.13675/j.cnki.tjjs.2303008
中图分类号：
学科分类号：
摘要：
In order to investigate the flow field characteristics of a five-nozzle combustor，the high-frequency PIV experiment was carried out to study the characteristics of the cold flow fields on the central plane of the combustor. Results were mainly focused on the impacts of inlet velocity and central nozzle swirl intensity on time-averaged flow field characteristics of central plane of the five-nozzle combustor. Experimental results indicate the main recirculation zones exist at the outlet of central and outer nozzles，and the corner recirculation zones exist between the outer nozzle and combustor wall. Adjacent swirling flows interact mutually. When swirl intensities of the five nozzles are the same，the shape and length of the main recirculation zones of the central and outer nozzles，the location of maximum reverse velocity and mixing point stay basically unchanged with the inlet velocity increasing from 10 m/s to 20 m/s. When the inlet velocity is 14.3 m/s ，the swirl intensity of the central nozzle increases from 0.63 to 0.84，the length of the main recirculation zone of the central nozzle increases，however，the length of the recirculation zone of the outer nozzle remains unchanged. The maximum reverse velocity of the main recirculation zone increases significantly，and the axial position of the maximum reverse velocity moves upstream to the nozzle outlet. The radial position of the mixing point is basically unchanged，and its axial position moves upstream closer to the nozzle outlet. © 2024 Journal of Propulsion Technology. All rights reserved.
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共 19 条
  • [1] LEFEBVRE H., Gas turbine combustion［M］, (1999)
  • [2] ZHANG B, RAO Z M，, Et al., Contributions of hydrodynamic features of a swirling flow to ther-moacoustic instabilities in a lean premixed swirl stabilized combustor［J］, Physics of Fluids, 31, 7, (2019)
  • [3] GOBBATO P，, MASI M, Et al., Calculation of the flow field and NOx emissions of a gas turbine combustor by a coarse computational fluid dynamics model ［J］, Energy, 45, 1, pp. 445-455, (2012)
  • [4] Comparison of the flow field of a swirl stabilized premixed burner in an annular and a single burner combustion chamber ［J］, Journal of Engineering for Gas Turbines and Power, 132, 7, (2010)
  • [5] CAI J, TACINA R., Multi-swirler aerodynamics：experimental measurements［C］, Salt Lake：37th AIAA Joint Propulsion Conference, (2001)
  • [6] (2007)
  • [7] CAI J, TACINA R., Multi-swirler aerodynamics：comparison of different configurations［C］, (2002)
  • [8] KAO Y H, JENG S M., Aerodynamics study of a linearly-arranged 5-swirler array［C］, Düssel-dorf：ASME Turbo Expo 2014：Power for Land，Sea，and Air, (2014)
  • [9] SAMARASINGHE J, Et al., The three-dimensional structure of swirl-stabilized flames in a lean premixed multi-nozzle can combustor ［J］, Journal of Engineering for Gas Turbines and Power, 138, 3, (2016)
  • [10] WORTH N A, DAWSON J R., Tomographic reconstruction of OH* chemiluminescence in two interacting turbulent flames［J］, Measurement Science and Technology, 24, 2, (2013)
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