Detonation Propagation in a Rotating Detonation Engine

用于通用航空的航空器涡轮喷气发动机在进气的机械压缩之后经由恒压燃烧操作。热力循环分析表明，以爆震燃烧方式进行燃烧，循环效率较高。脉冲爆震发动机的研究已经取得了很大的进展，最近世界范围内的研究已经转向旋转爆震发动机（RDE）的发展。RDE更紧凑，并且在稳定条件下操作，因此比其脉冲模式对应物具有更少的噪声和振动问题。在RDE中，燃料和氧化剂通过一端（推力壁）上的孔矩阵连续喷射到环形燃烧室中。爆震波在环形燃烧器周围传播，当其进入燃烧室时消耗燃料，并且燃烧产物膨胀出燃烧室的开口端，从而产生推力。大多数研究计划涉及示范发动机的设计和测试，其中测量仅限于燃烧室压力和爆震波速度。虽然燃料氧化剂混合的重要性已被认识到，但在这方面所做的实验工作很少。建议的研究计划的目的是调查的影响，燃料-氧化剂混合过程中的稳定性和结构的爆震波在一个单一的拍摄，线性RDE。线性RDE本质上是一个未包裹的RDE，允许使用最先进的纹影可视化和烟灰箔技术。这些技术在过去十年中在我的实验室中已经完善，与工业爆炸安全研究有关。** 这项研究很重要，因为混合和燃烧的直接可视化将使优化燃油/空气进气系统设计成为可能，这是RDE的核心。研究的成果将是一个线性RDE的发展，将用于驱动原型环形RDE的设计。实验工作将得到使用开源计算流体动力学（CFD）代码OpenFoam进行的数值模拟的支持。线性RDE将是一个重要的测试工具，它将为代码开发提供有价值的数据。该项目的结果将被世界各地的研究人员用于RDE开发，包括实验和计算。HQP将接受使用最先进的可视化和计算技术的培训。航空航天工业有兴趣开发新的紧凑高效推进系统，加拿大发动机公司的子公司，如普惠公司，西门子公司和通用电气公司将受益于这项技术的进步，以及飞机制造商庞巴迪公司。国防部非常感兴趣，因为他们已经与澳大利亚、英国和美国签订了一项技术合作计划，处理RDE问题。**

Aircraft turbo jet engines used for general aviation operate via constant pressure combustion following mechanical compression of the intake air. Thermodynamic cycle analysis shows that the cycle efficiency is higher if combustion proceeds via the detonation mode of combustion. Significant research effort has gone into developing a pulse-mode detonation engine, recent efforts world-wide have switched to the development of a Rotating Detonation Engine (RDE). RDEs are more compact and operate under steady conditions and therefore have less noise and vibration issues than their pulsed mode counterparts. In a RDE, the fuel and oxidizer are injected continuously into an annular combustion chamber through a matrix of holes on one end (the thrust wall). A detonation wave propagates around the annular combustor consuming the fuel as it enters the combustion chamber, and the combustion products expand out the open-end of the chamber producing thrust. Most research programs involve the design and testing of demonstration engines, where measurements are limited to combustion chamber pressure and detonation wave velocity. Although the importance of the fuel oxidizer mixing has been recognized, there has been very little experimental work done in this area. The objective of the proposed research program is to investigate the influence of the fuel-oxidizer mixing process on the stability and structure of the detonation wave in a single-shot, linear RDE. A linear RDE is essentially an unwrapped RDE that permits the use of state-of-the-art schlieren visualization and soot foil technique. These are techniques that have been perfected in my laboratory over the last decade in connection with industrial explosion safety research. ******This research is important because the direct visualization of the mixing and combustion will make it possible to optimize the fuel/air intake system design, which is the heart of the RDE. The outcomes of the research will be the development of a linear RDE that will be used to drive the design of prototype annular RDE. The experimental work will be supported by numerical simulations carried out using the open-source computational fluid dynamics (CFD) code OpenFoam. The linear RDE will be an important test facility that will produce valuable data for code development. The results from this project will be used by researchers around the world working on RDE development, both experimental and computational. HQP will be trained in the use of state-of-the-art visualization and computational techniques. The aerospace industry is interested in developing new compact efficient propulsion systems, and Canadian engine company subsidiaries such as Pratt and Whitney, Siemens, and GE would benefit from the advancement of this technology, as well as the aircraft constructor Bombardier. The Department of National Defence is keenly interested as they have entered a Technical Cooperation Program dealing with RDEs with Australia, UK, and the USA. **