摘要
连续旋转爆震发动机在热循环效率方面比等压燃烧发动机具有明显优势，它点火后即可连续工作并能提供稳定的推力，具有非常广阔的应用前景。本文运用理论分析、实验研究、数值模拟等手段，重点对H_2/air连续旋转爆震波的结构、传播模态及自持传播机理进行了深入系统的研究。
论文设计加工了两套不同喷注方式的模型发动机，并研制了具有两级收缩的热射流管用于发动机点火起爆。研究了点火时机、混合效果、点火方式对H_2/O2热射流生成过程的影响，并对所生成的热射流状态进行了测量。对比研究了热射流切向和垂直喷射、普通火花塞持续点火、高能火花塞单次点火四种起爆方案，结果表明热射流切向喷射方式的起爆效果最好，在较宽的热射流能量范围内，都可成功起爆模型发动机。
实验共发现了两种爆震波传播模式：同向传播模式和对撞传播模式。
同向传播模式的研究结果表明：燃烧室内存在单个或多个爆震波头，同一时刻所有爆震波头的传播方向相同。在部分实验过程中，爆震波传播方向会发生改变；爆震波头个数与混合气总流量相关，随总流量的增大而增多。与双波模态相比，单波模态时的爆震波高度更高、传播速度更大；实验过程中，不同周期内的爆震波瞬时传播速度和峰值压力存在一定的差异；时间平均后的流场参数沿圆周方向分布均匀。
对撞传播模式的研究结果表明：燃烧室内存在两个爆震波头，它们传播方向相反，发生周期性对撞。在燃烧室顶部能否形成可燃气体层是实现该传播模式的关键；高频压力的振荡特性跟测压点与对撞点的夹角相关；双波对撞会产生高压力峰值，且所产生的推力沿圆周方向分布不均匀，应尽量避免该燃烧模式。
论文针对同向模式下的爆震波传播过程开展了系统研究。发现存在一定的工况边界，在该工况边界外连续旋转爆震波无法维持传播；研究了连续旋转爆震燃烧对推进剂喷注过程的影响，提出了混合气实际当量比的计算方法。统计了连续旋转爆震波实验传播速度与理论速度间的亏损值，发现当速度亏损大于17%时，爆震波难以自持传播；详细研究了侧向膨胀因素对连续旋转爆震波传播速度亏损的影响，单、双波模态时估算的由侧向膨胀所引起的速度亏损分别为4.6%-12%和6%-15%。发现自持工况边界处的速度亏损理论估算值与实验值接近，这说明连续旋转爆震波的传播速度亏损主要由侧向膨胀引起。
开展了连续旋转爆震发动机应用研究，验证了通过改变局部喷注压降实现推力矢量调节的可行性；对比研究了燃烧室长度、宽度、尾喷管等因素对发动机性能的影响。结果表明，燃烧室长度和宽度对发动机性能影响较小，而加装尾喷管能在一定程度上提高其比冲性能。
The thermodynamic efficiency of continuous rotating detonation engine (CRDE) islarger than that of conventional constant-pressure combustion engines. CRDE couldoperate continuously just with one initiation. Due to the high rotating frequency, CRDEcould produce a roughly stable thrust, so it has huge potential benefits. Using acombination of theoretical analysis, experimental observation and numerical simulation,the flow-field structure, rotating mode and lasting mechanism of H_2/air continuousrotating detonation wave have been studied.
Based on the present CRDE research results, two continuous rotating detonationcombustors are desgined and constructed with different propellant injection methods,such as injector-injector and slot-injector collision methods. A hotshot tube is desginedand constructed too, which has two convergent sections. The H_2/O2hotshot jet formingprocess is studied, and the influences of ignition opportunity, H_2/O2mixing quality andignition method have been discussed. Through lots of tests, a reliable program is gained,and the intensity of the hotshot jet has been measured quantitatively. Four CRDEinitiation methods have been discussed, and H_2/O2hotshot jet tangential injectionmethod has the best reliability. Using this method, CRDE can be initiated successfullyat a wide range of hotshot jet intensity.
Lots of tests have been carried out, and there are two detonation wave rotatingmodes, which are one-direction mode and two-wave collision mode.
For the one-direction rotating mode, all the detonation waves propagate along thesame direction at the same time. But the propagation direction may change during thetest process under some experiment conditions. The number of detonation waves aremainly influenced by the total mass flow rate of the propallents. The values of heightand propagation velocity of detonation wave in one-wave mode are larger than that oftwo-wave mode. For experimental results, the detonation wave propagates unstably, andits propagation velocities and peak pressure values are different from one period toanother. Within several periods, the flow-field parameters are time averaged, and theaverage parameter values along the azimuthal direction are nearly the same.
For the two-wave collision mode, there are two detonation waves propagatingalong opposite directions in the combustor, colliding with each other periodically. Torealize this rotating mode, there should be an annular zone of fresh H_2/air mixtureslocated at the top of the combustor. The oscillating characteristics of the PCB results areanalyzed, and it is mainly influenced by the azimuthal angle between the pressuremeasurement point and the detonation wave collision point. Two-wave collision canlead to high pressure values, and the average flow-field parameters along the azimuthaldirection are different from each other. So this rotating mode should be avoided in thedetonation engines.
Through changing test conditions, lots of tests have been carried out, and thedetonation wave lasting condition boundaries are gained. During the test, the propellantinjection process has been influenced by the rotating detonation wave. Considering thisprocess, the actual equivalence ratio of the H_2/air mixture is calculated, and thedetonation wave propagation velocity deficits are studied. For CRDE tests, when thedetonation wave propagation velocity deficit is larger than17%, the detonation wavecould not propagate continuously. Influences of the lateral expansion on the detonationwave structure and propagation process are detailed, and the calculation method ofpropagation veloctiy deficit caused by lateral expansion is deduced. For one-wave mode,the velocity deficit calculated by this method is4.6%-12%, and the corresponding valueis6%-15%for two-wave mode. Under the critical test condition, the velocity deficitcalculated by lateral expansion is close to17%, which shows that the velocity deficit ofthe continuous rotating detonation wave is mainly caused by the lateral expansioneffect.
Investigations on the CRDE application are also carried out. Based ontwo-dimensional numerical simulation, the thrust vectoring ability of CRDE isdemonstrated. The influences of combustor geometric factors on the engineperformance have been analyzed by means of three-dimensional numerical simulation.The specific impulse performance can be improved by using a nozzle.
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