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DNS analysis of the effects of combustion on turbulence in a supersonic H2/air jet flow

机译：DNS分析超音速H2 /空气射流中燃烧对湍流的影响

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In this paper, the effects of combustion on turbulence features are investigated by direct numerical simulation (DNS) of supersonic round turbulent hydrogen jet flows. Two DNS cases are conducted: the one is combustion hydrogen/air jet and the other is non-combustion jet with the same components as a comparison case. In the DNS, the supersonic jet consists of 85% hydrogen and 15% nitrogen in volume with temperature of 305 K and jet velocity of 900 m/s. The ambient air velocity is 20 m/s and temperature is 1150 K. The Reynolds numbers based the jet exit diameter and hydrogen jet velocity both are 22000 and the jet Mach numbers both are 1.2. The DNS results show that occurrence of combustion significantly delays the transition of the jet flow, and results in a 38% decrease in the peak of turbulent kinetic energy, compared with the non-combustion jet flow. The decreasing of the Reynolds number due to the heat release is considered as the main reason. Compared with the non-combustion jet flow, the combustion jet flow has more complete coherent vortex rings in the early stage. In addition, the positive and minus energy fluxes of combustion jet flow are always larger than that of non-combustion jet flow. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：本文通过超声速圆形湍流氢射流的直接数值模拟（DNS）研究了燃烧对湍流特征的影响。进行了两种DNS案例：一种是燃烧氢/空气喷射，另一种是非燃烧喷射，其组成与比较例相同。在DNS中，超音速喷射器的体积为85％的氢气和15％的氮气，温度为305 K，喷射速度为900 m / s。环境空气速度为20 m / s，温度为1150K。基于射流出口直径和氢气射流速度的雷诺数均为22000，射流马赫数均为1.2。 DNS结果表明，与非燃烧射流相比，燃烧的发生显着延迟了射流的过渡，并使湍动能峰值降低了38％。雷诺数由于放热而降低被认为是主要原因。与非燃烧射流相比，燃烧射流在早期具有更完整的相干涡环。另外，燃烧喷射流的正和负能量通量总是大于非燃烧喷射流的正和负能量通量。 （C）2019 Elsevier Masson SAS。版权所有。

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