The formation of a number of co- and counter-rotating coherent combustion wave fronts is the hallmark feature of the Rotating Detonation Engine (RDE). The engineering implications of wave topology are not well understood nor quantified, especially with respect to parametric changes in combustor geometry, propellant chemistry, and injection and mixing schemes. In this article, a modeling framework that relates the time and spacial scales of the RDE to engineering performance metrics is developed and presented. The model is built under assumptions of backpressure-insensitivity and nominally choked gaseous propellant injection. The Euler equations of inviscid, compressible fluid flow in one dimension are adapted to model the combustion wave dynamics along the circumference of an annular-type rotating detonation engine. These adaptations provide the necessary mass and energy input and output channels to shape the traveling wave fronts and decaying tails. The associated unit processes of injection, mixing, combustion, and exhaust are all assigned representative time scales necessary for successful wave propagation. We find that the separation, or lack of, these time scales are responsible for the behavior of the system, including wave co- and counter-propagation and bifurcations between these regimes and wave counts. Furthermore, as there is no imposition of wave topology, the model output is used to estimate the net available mechanical work output and thermodynamic efficiency from the closed trajectories through pressure-volume and temperature-entropy spaces. These metrics are investigated with respect to variation in the characteristic scales for the RDE unit physical processes.
Endwall and leading-edge film cooling of turbine blades in a hydrogen-fueled rotating detonation combustor-turbine coupled system
Ningbo Institute of Materials Technology and Engineering, Chinese Academy of Sciences（中国科学院宁波材料技术与工程研究所）；University of Chinese Academy of Sciences（中国科学院大学）；Institute for Energy Research, Jiangsu University（江苏大学能源研究所）
Application of a Pressured-Based OpenFOAM Solver for Rotating Detonation Engines
Korea Advanced Institute of Science and Technology（韩国科学技术院）；New York University Abu Dhabi（纽约大学阿布扎比分校）；Tandon School of Engineering, New York University（纽约大学坦登工程学院）
Investigation of Mist and Air Film Cooling in a Two-Phase Rotating Detonation Combustor with Liquid Kerosene
Zhejiang Key Laboratory of Laser Extreme Manufacturing for Difficult-to-Machine Materials, Ningbo Institute of Materials Technology and Engineering, Chinese Academy of Sciences（中国科学院宁波材料技术与工程研究所）；University of Chinese Academy of Sciences（中国科学院大学）
The criterion on the Propulsive Balance of Oblique Detonation Engine
斜爆轰发动机（ODE）以其高的热效率和紧凑的结构在高超声速飞行中具有明显的优势。近年来，它已成为世界各国的研究热点。本研究的目的是推导出一个常微分方程的推进平衡判据，从中我们可以明确地找到控制推进性能的关键参数。建立了由进气道、等截面燃烧室和扩张喷管组成的常微分方程物理模型。推导了计算扩张喷管产生的推力和进气道产生的压阻的数学方程。然后得到ODE的净推力。该判据清楚地表明，发动机进、出口处的静温是一个非常重要的参数。进气出口温度越低，比冲越高。利用这些方程计算了化学计量比的H2/空气混合气和碳氢/空气混合气的ODE比冲。结果表明，在Ma 8 ~ Ma 15的范围内，ODE都能获得正的净推力。
Numerical Investigation of Mach 10 Kerosene-Fueled Oblique Detonation Waves at Different Flight Altitudes
Institute of Mechanics, Chinese Academy of Sciences（中国科学院力学研究所）；School of Engineering Science, University of Chinese Academy of Sciences（中国科学院大学工程科学学院）
Comparative Numerical Study of Film Cooling Strategies for Thermal Protection of a Kerosene-Fueled Oblique Detonation Combustor
Ningbo Institute of Materials Technology and Engineering, Chinese Academy of Sciences（中国科学院宁波材料技术与工程研究所）；University of Chinese Academy of Sciences（中国科学院大学）
