Development and experimental investigation of a piloted, rotating detonation wave combustor (RDWC) designed for natural gas and air propellants is presented in the current paper. The pilot stage was designed to operate with natural gas and oxygen to extend the main stage RDWC range of operability, control its dynamics, and scale the system thermal power. The main chamber can operate with oxygen enrichment across a range of oxygen mass fraction in oxidizer flow of 23.2% (air) to 35%. An annular sting design for natural gas injection was chosen for the main stage of the RDWC to both minimize injection distance and provide modularity in injector design for future testing. Initial experiments were performed with the main chamber operating without the pilot at high pressure (10 atm) and air preheat temperatures up to 650 K. High- and low-frequency pressure measurements are analyzed to understand performance and chamber dynamics. While high-amplitude chamber dynamics with p′/pc = 60% were observed in preliminary experiments, stable detonative behavior in the main chamber has not yet been demonstrated, and further testing must be completed to define RDWC operability range before adding pilot stage operation.
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机译：本文介绍了一种设计用于天然气和空气推进剂的先导旋转爆轰波燃烧器（RDWC）的开发和实验研究。中试台旨在与天然气和氧气一起使用，以扩展主级RDWC的可操作性范围，控制其动态特性并缩放系统热功率。主腔室可在氧气流量范围为23.2％（空气）至35％的氧气质量分数范围内富集氧气。为RDWC的主要阶段选择了用于天然气喷射的环形ing设计，以最小化喷射距离并为将来的测试提供喷射器设计的模块化。初始实验是在主腔室不使用先导阀且在高压（10 atm）和空气预热温度高达650 K的情况下进行的。分析了高频和低频压力测量值以了解性能和腔室动态。尽管在初步实验中观察到p'/ pc = 60％的高振幅腔动力学，但尚未证明主腔中具有稳定的爆炸行为，在添加试验级操作之前，必须完成进一步的测试以定义RDWC的可操作范围。
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