Experimental research on the rotating detonation in gaseous fuels–oxygen mixtures
Experimental research on the rotating detonation in gaseous fuels–oxygen mixtures
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DOI：
10.1007/s00193-011-0298-y
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发表时间：
2011-01
期刊：
影响因子：
2.2
通讯作者：
J. Kindracki;Piotr Wola;ski;Z. Gut
中科院分区：
文献类型：
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作者：
J. Kindracki;Piotr Wola;ski;Z. Gut
本文对旋转爆轰进行了实验研究。这项研究的重点是在火箭发动机中使用旋转起爆的可能性。本文的研究分为两部分：第一部分研究了燃料-氧气混合物中旋转爆轰的起爆；第二个目的是确定传播稳定性的范围作为一个函数的腔室压力，成分，和几何。并在后期确定了推力和比冲。本文只描述了丰富的混合物，因为在火箭燃烧室中使用这种成分可以最大限度地提高比冲和推力。在实验中，研究了两种几何形状：圆柱形和圆柱形，后者可以用一个简单的气刺喷管模拟。甲烷、乙烷和丙烷被用作燃料。给出了管汇和腔室内的压力-时间过程。由测得的压力峰值计算出的推力时间分布和爆轰速度如图所示。为了验证旋转爆震火箭发动机作为高能气体发生器的性能，设计、制造了一个简单的发动机模型并进行了测试。在试验中，将发动机模型连接到倾卸箱上。该解决方案可以模拟从16公里高空到海平面的不同环境条件。得到的压力比冲量为。1.2 bar和3.5左右的小喷嘴膨胀比接近1500 m/s。
An experimental study on rotating detonation is presented in this paper. The study was focused on the possibility of using rotating detonation in a rocket engine. The research was divided into two parts: the first part was devoted to obtaining the initiation of rotating detonation in fuel–oxygen mixture; the second was aimed at determination of the range of propagation stability as a function of chamber pressure, composition, and geometry. Additionally, thrust and specific impulse were determined in the latter stage. In the paper, only rich mixture is described, because using such a composition in rocket combustion chambers maximizes the specific impulse and thrust. In the experiments, two kinds of geometry were examined: cylindrical and cylindrical-conic, the latter can be simulated by a simple aerospike nozzle. Methane, ethane, and propane were used as fuel. The pressure–time courses in the manifolds and in the chamber are presented. The thrust–time profile and detonation velocity calculated from measured pressure peaks are shown. To confirm the performance of a rocket engine with rotating detonation as a high energy gas generator, a model of a simple engine was designed, built, and tested. In the tests, the model of the engine was connected to the dump tank. This solution enables different environmental conditions from a range of flight from 16 km altitude to sea level to be simulated. The obtained specific impulse for pressure in the chamber of max. 1.2 bar and a small nozzle expansion ratio of about 3.5 was close to 1,500 m/s.