Numerical Study on Flow Characteristics of Serpentine Convergent-Divergent Nozzle

被引：0
|
作者：
Zhou L. [1 ]
Meng Y.-B. [1 ]
Wang Z.-X. [1 ]
机构：
[1] Shaanxi Key Laboratory of Internal Aerodynamics in Aero-Engine, School of Power and Energy, Northwestern Polytechnical University, Xi'an
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2021年 / 42卷 / 01期
关键词：
Aerodynamic performance; Exit area ratio; Flow characteristic; Nozzle pressure ratio; Serpentine convergent-divergent nozzle;
D O I：
10.13675/j.cnki.tjjs.200271
中图分类号：
学科分类号：
摘要：
In order to investigate the flow mechanism of serpentine convergent-divergent nozzle, the numerical simulation on the flow characteristics of serpentine convergent-divergent nozzle with different nozzle pressure ratio (NPR) and exit area ratio of serpentine convergent duct (A72/A8) had been performed. The results show that with the increase of NPR in the highly over-expanded conditions of serpentine convergent-divergent nozzle, the unsymmetrical flow separation turned into symmetrical flow separation and the λ shock turned into Mach disk, which bringed about the decrease of aerodynamic performance and vector angle. As NPR continued to rise, shock waves moved toward the nozzle outlet, and gradually transformed into an expansion wave. As a result, the aerodynamic performance increased, and the vector angle remained unchanged after decreasing to 0°. Under the low observable qualifications of totally shielding the high-temperature components, the change of A72/A8 notably impacted on the flow characteristic in the convergent duct, mainly reflecting in the local acceleration and secondary flow in the serpentine convergent duct. And the performance of the serpentine convergent-divergent nozzle increased with the increment of A72/A8. While A72/A8 increased to 1.8, the flow separation occurred on the upper wall of the first serpentine duct, inducing the notable decrease of aerodynamic performance. © 2021, Editorial Department of Journal of Propulsion Technology. All right reserved.
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页码：103 / 113
页数：10
相关论文
共 21 条
  • [1] An C H, Kang D W, Baek S T, Et al., Analysis of Plume Infrared Signatures of S-Shaped Nozzle Configurations of Aerial Vehicle, Journal of Aircraft, 53, 6, pp. 1768-1778, (2016)
  • [2] Cheng W, Wang Z X, Zhou L, Et al., Influences of Shield Ratio on the Infrared Signature of Serpentine Nozzle, Aerospace Science and Technology, 71, pp. 299-311, (2017)
  • [3] 4, pp. 1-4
  • [4] 11
  • [5] Sun X L, Wang Z X, Zhou L, Et al., Experimental and Computational Investigation of Double Serpentine Nozzle, Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering, 229, 11, pp. 2035-2050, (2015)
  • [6] Sun X L, Wang Z X, Zhou L, Et al., Influences of Design Parameters on a Double Serpentine Convergent Nozzle, Journal of Engineering for Gas Turbines & Power Transactions of the ASME, 138, 7, pp. 1-16, (2016)
  • [7] Du L W, Liu Y H, Li T., Numerical Predictions of Scarfing on Performance of S-Shaped Nozzle with Asymmetric Lobe, Journal of Propulsion and Power, 3, 2, pp. 604-618, (2015)
  • [8] Rajkumar P, Sekar T C, Kushar A, Et al., Flow Characterization for a Shallow Single Serpentine Nozzle with Aft Deck, Journal of Propulsion and Power, 33, 5, pp. 1130-1139, (2017)
  • [9] Sekar T C, Kushari A, Mody B, Et al., Fluidic Thrust Vectoring Using Transverse Jet Injection in a Converging Nozzle with Aft-Deck, Experimental Thermal and Fluid Science, 86, pp. 189-203, (2017)
  • [10] Shan Y, Zhou X M, Tan X M, Et al., Parametric Design Method and Performance Analysis of Double S-Shaped Nozzles, International Journal of Aerospace Engineering, 2, pp. 1-24, (2019)
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