Demonstration of mode transition in a scramjet combustor
Demonstration of mode transition in a scramjet combustor
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DOI：
10.2514/3.23653
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发表时间：
1993-07
影响因子：
1.9
通讯作者：
G. Sullins
中科院分区：
文献类型：
--
作者：
G. Sullins
直接连接燃烧室硬件已经在约翰霍普金斯大学应用物理实验室（JHU/APL）的Avery推进研究实验室（APRL）组装，用于研究氢燃料超燃冲压发动机燃烧室。测试硬件设计用于在模拟马赫数5到马赫数8的飞行条件下进行测试。这是用H2燃料和补充O2的燃烧加热器完成的。空气、H2和O2的流量都是通过电脑控制的数字阀门提供的。该系统允许条件快速变化，并且在整个测试过程中保持非常稳定的流量。最近进行了试验，在试验过程中系统地改变流速，以模拟从M = 5.9到6.2的加速度。在此加速过程中，燃料-空气等效比保持不变，并且燃烧室从具有在喷射平面产生亚音速流动的燃烧前激波系统的双模冲压发动机过渡到没有燃烧前激波系统的超燃冲压发动机。这些测试的结果，以及硬件和控制系统的描述。
Direct-connect combustor hardware has been assembled at the Avery Propulsion Research Laboratory (APRL) of the Johns Hopkins University Applied Physics Laboratory (JHU/APL) to investigate a hydrogen-fueled scramjet combustor. The test hardware was designed to perform tests at simulated Mach 5 to Mach 8 flight conditions. This is done using a combustion heater with H2 fuel and makeup O2. The air, H2 and O2 flow rates are all supplied through computer-controlled digital valves. This system allows rapid changes in conditions and very steady flow rates can be maintained throughout the test. Recently, tests were performed in which the flow rates were systematically varied during the test to simulate an acceleration from M = 5.9 to 6.2. During this acceleration the fuel-air equivalence ratio was held constant and the combustor transitioned from a dual mode ramjet with a precombustion shock system creating subsonic flow at the injection plane, to a scramjet with no precombustion shock system. The results of these tests are presented along with descriptions of the hardware and control systems.