Experimental Research of Performance of Combined Cycle Rotating Detonation Rocket-Ramjet Engine (original) (raw)
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Combustion Engines, 2022
In the paper short information about advantages of introduction of detonation combustion to propulsion systems is briefly discussed and then research conducted at the Łukasiewicz-Institute of Aviation on development of the rotating detonation engines (RDE) is presented. Special attention is focused on continuously rotating detonation (CRD), since it offers significant advantages over pulsed detonation (PD). Basic aspects of initiation and stability of the CRD are discussed. Examples of applications of the CRD to gas turbine and rocket engines are presented and a combine cycle engine utilizing CRD are also evaluated. The world's first rocket flight powered by liquid propellant detonation engine is also described.
8TH BSME INTERNATIONAL CONFERENCE ON THERMAL ENGINEERING
A detonation is a combustion wave that propagates at supersonic speed (2~3 km/s) in a combustible mixture. There are many fundamental studies of detonation waves and detonation engine systems. The detonation cycle has a higher thermal efficiency than a conventional constant-pressure combustion cycle. Therefore, it is expected that a highefficiency propulsion system can be realized using detonation waves.A rotating detonation engine (RDE) uses continuous detonation propagating at a bottom in an annular combustor. As detonation waves propagate at a supersonic speed only in the bottom region of the RDEs, the combustor can be shortened. However, the combustor needs cooling system due to high heat flux to the combustor wall.In this experimental study, we performed combustion tests of RDE system using gaseous ethylene and oxygen as the propellant. This RDE system performance will also be demonstrated in space environment by the sounding rocket. We measured the combustor pressure, temperatures, heat flus, mass flow rate and thrust. The RDE system used in this study is shown in Figure 1. We performed the long-duration rotating detonation engine combustion tests for at sea level condition. The stable trust histories were obtained.
Experimental validation of rotating detonation for rocket propulsion
Scientific Reports
Space travel requires high-powered, efficient rocket propulsion systems for controllable launch vehicles and safe planetary entry. Interplanetary travel will rely on energy-dense propellants to produce thrust via combustion as the heat generation process to convert chemical to thermal energy. In propulsion devices, combustion can occur through deflagration or detonation, each having vastly different characteristics. Deflagration is subsonic burning at effectively constant pressure and is the main means of thermal energy generation in modern rockets. Alternatively, detonation is a supersonic combustion-driven shock offering several advantages. Detonations entail compact heat release zones at elevated local pressure and temperature. Specifically, rotating detonation rocket engines (RDREs) use detonation as the primary means of energy conversion, producing more useful available work compared to equivalent deflagration-based devices; detonation-based combustion is poised to radically im...
Present Status of Pulse and Rotating Detonation Engine Research
2015
A self-sustained detonation wave propagates at the speed of 2–3 km/s, and it induces the exothermic chemical reaction in a tube filled with a premixed gas. An engine with a detonation wave intermittently generated in a straight tube is called a pulse detonation engine (PDE) [1–7], and an engine with a detonation wave rotating continuously in annular gap is called a rotating detonation engine (RDE) [8]. In the detonation combustion process, the reactant is compressed by the shock wave, and it is recombined to be the product at high temperature (the generated entropy for the product is small). Therefore, engines that use a detonation cycle have greater thermal efficiency than engines with constant-pressure combustion cycle. This cycle analysis was done by Zel’dovich [9] and has been confirmed by many researchers using various gaseous models [10–12].
Numerical Investigation of Rotating Detonation Engine Propulsive Performance
Combustion Science and Technology, 2010
Rotating detonation engines are widely studied because of their compact configurations and high thermal cycle efficiency. For briefty, most of the numerical simulations of rotating detonation engines used premixed reactant mixtures. The rotating detonation waves under non-premixed condition are not studied enough. Here, a series of three-dimensional numerical simulations of a rotating detonation engine under both premixed and non-premixed conditions using H 2 /air mixture are performed. The explicit formulation of density-based solver in ANSYS Fluent is used to perform the simulations. Two total mass flow rates of 272.3 g/s and 500 g/s are selected. When the total mass flow rate is 272.3 g/s, the engine operates at single-wave mode under both premixed and non-premixed conditions. When the total mass flow rate is 500 g/s, the engine operates at single-wave mode under premixed condition. While under non-premixed condition, a spontaneous formation of dual-wave mode is observed. This case agrees well with the phenomenon observed in experiments that as the total mass flow rate increases, the number of rotating detonation waves tends to increase. Pressure waves caused by the high pressure behind the detonation waves can propagate upstream to the H 2 and air plenums.
Detonation Engine Performance Comparison Using First and Second Law Analyses
46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2010
A performance comparison between airbreathing pulsed detonation engine (PDE) and rotating detonation wave engine (RDWE) concepts is made. The flight speed range used for the analysis is approximately Mach 1-5, which is typically thought to be where these concepts are viable and perhaps competitive with each other and Brayton cycle engines. Since the RDWE is ideally capable of operation with a steady state inlet and nozzle, a PDE model with similar steady state systems was developed. The comparison shows a PDE is more efficient at low supersonic speeds, but the relative RDWE performance gradually increases until it becomes comparable. The thermodynamic cycles of these detonationbased engines have been examined in detail using the Second Law to show the losses associated with mixing and purging. Additionally, the combination of an exergy analysis with First Law performance benchmarks proves to be a useful approach for optimization since sources of losses and component interrelationships are easier to identify.
Preliminary design of a pulsed detonation based combined cycle engine
ISABE, 2001
Results of a recent investigation in the design of a single flow path combined cycle engine using periodic detonation waves are presented here. Four modes of operation are used in a sample SSTO trajectory in this preliminary design (sketched in Fig. [1]): (1) An ejector augmented pulsed detonation rocket for take off to moderate supersonic Mach numbers (2) A pulsed normal detonation wave mode at combustion chamber Mach numbers less than the Chapman-Jouguet Mach number, (3) An oblique detonation wave mode for Mach numbers in the airbreathing regime that are higher than the Chapman-Jouguet Mach number, and (4) A pure Pulsed Detonation Rocket (PDR) mode of operation at high altitude. These modes utilize a single flow path, in which an array of detonation tubes is placed. The tubes fire sequentially in such a manner as to make the maximum use of the incoming air mass and provide the smoothest possible operation of the device. These tubes could alternately be embedded in load bearing struts. Performance estimates based on the stream thrust approach have been obtained from a time averaged ideal cycle analysis with corrections from CFD results. Suggestions for performance enhancement are outlined.
INCAS BULLETIN
Pulse Detonation Engine (PDE), is an emerging and promising propulsive technology all over the world in the past few decades. A pulse detonation engine (PDE) is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer mixture. Theoretically, a PDE can be operate from subsonic to hypersonic flight speeds. Pulsed detonation engines offer many advantages over conventional air-breathing engines and are regarded as potential replacements for air-breathing and rocket propulsion systems, for platforms ranging from subsonic unmanned vehicles, long-range transportation, high-speed vehicles, space launchers to space vehicles. This article highlights the operating cycle of PDE, starting with the fuel-oxidizer mixture, combustion and Deflagration to detonation transition (DDT) followed by purging. PDE combustion process, a unique process, leads to consistent and repeatable detonation waves. This pulsed detonation combustion process causes rapid burning of the fuel...