Development of a Large Pulse Detonation Engine Demonstrator (original) (raw)
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Experiences in Testing of a Large-Scale, Liquid-Fueled, Air-Breathing, Pulse Detonation Engine
47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2011
A large-scale pulse detonation engine utilizing air and kerosene was constructed to demonstrate its practical implementation. Testing this ground demonstrator revealed successes and areas requiring improvement in the design, fabrication, installation and actual testing of a large PDE. Many of the challenges of translating smaller, single shot experiments have been overcome in this implementation of a 4 inch diameter detonation engine. This paper will discuss the experiences in testing the engine as a whole, and also on some of these subsystems involved. Full testing has not been completed, but successful operation provides a positive outlook for further innovation and modification.
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...
Review Article Review on Recent Advances in Pulse Detonation Engines
Pulse detonation engines (PDEs) are new exciting propulsion technologies for future propulsion applications. The operating cycles of PDE consist of fuel-air mixture, combustion, blowdown, and purging. The combustion process in pulse detonation engine is the most important phenomenon as it produces reliable and repeatable detonation waves. The detonation wave initiation in detonation tube in practical system is a combination of multistage combustion phenomena. Detonation combustion causes rapid burning of fuel-air mixture, which is a thousand times faster than deflagration mode of combustion process. PDE utilizes repetitive detonation wave to produce propulsion thrust. In the present paper, detailed review of various experimental studies and computational analysis addressing the detonation mode of combustion in pulse detonation engines are discussed. The effect of different parameters on the improvement of propulsion performance of pulse detonation engine has been presented in detail in this research paper. It is observed that the design of detonation wave flow path in detonation tube, ejectors at exit section of detonation tube, and operating parameters such as Mach numbers are mainly responsible for improving the propulsion performance of PDE. In the present review work, further scope of research in this area has also been suggested.
Numerical simulation and performances evaluation of the pulse detonation engine
MATEC Web of Conferences, 2018
A pulse detonation engine (PDE) is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer mixture. The engine is pulsed because the mixture must be renewed in the combustor between each detonation wave. Theoretically, a PDE can operate from subsonic up to hypersonic flight speed. Pulsed detonation engines offer many advantages over conventional propulsion systems and are regarded as potential replacements for air breathing and rocket propulsion systems, for platforms ranging from subsonic unmanned vehicles, long range transports, high-speed vehicles, space launchers to space vehicles. The article highlights elements of the current state of the art, but also theoretical and numerical aspects of these types of unconventional engines. This paper presents a numerical simulation of a PDE at h=10000 m with methane as working fluid for stoichiometric combustion, in order to find out the detonation conditions.
AN EXPERIMENTAL STUDY ON KEROSENE BASED PULSE DETONATION ENGINE
The paper summarizes the experimental study on kerosene based pulse detonation engine in a tube for three different equivalence ratios. The kerosene was vaporized in a pre-evaporator before injected into combustion chamber. Pre-heated air was injected through a nozzle into the detonation tube. The charged tube was electrically ignited near the injector end. To enhance the DDT and to reduce the transition distance Shchelkin spiral was used inside the tube. Comparison of measured pressure at different locations of the tube with the CEA values were made that confirms to have crossed the CJ point and provide a stable detonation.
PULSE DETONATION ENGINE TECHNOLOGY: AN OVERVIEW
Pulse detonation is a propulsion technology that involves detonation of fuel to produce thrust more efficiently than current engine systems. By library research and an interview with Dr. Roger Reed of the Metals and Materials Engineering Department of the University of British Columbia, it is shown that Pulse Detonation Engine (PDE) technology is more efficient than current engine types by virtue of its mechanical simplicity and thermodynamic efficiency. As the PDE produces a higher specific thrust than comparable ramjet engines at speeds of up to approximately Mach 2.3, it is suitable for use as part of a multi-stage propulsion system. The PDE can provide static thrust for a ramjet or scramjet engine, or operate in combination with turbofan systems. As such, it sees potential applications in many sectors of the aerospace, aeronautic, and military industries. However, there remain engineering challenges that must be overcome before the PDE can see practical use. Current methods for initiating the detonation process need refinement. To this end, both Pratt & Whitney and General Electric have developed different processes to accomplish this. Also, current materials used in jet engines, such as Nickel-based super-alloys, are inadequate to withstand the extreme heat and pressure generated by the detonation cycle. Therefore, new materials must be developed for this purpose.
A Characterized Status Report on Pulse Detonation Engine
INCAS BULLETIN
Pulse Detonation Engine (PDE), is an exciting propulsion technology for the future and has been able to seek considerable attention over the last era. It has the potential to work efficiently in the modern cosmos. It works on a Humphrey cycle offering a great opportunity, which outweighs the conventional Brayton cycle. The operating cycle of PDE starts with the fuel-oxidizer mixture, combustion and DDT followed by purging. The PDE combustion process, which is a unique process, leads to consistent and repeatable detonation waves. This pulsed detonation combustion process causes rapid burning of the fuel-oxidizer mixture, which cannot be seen in any other combustion process as it is a thousand times faster than any other mode of combustion. PDE not only holds the capability of running effectively up to Mach 5 but it also changes the technicalities in space propulsion. The present study deals with the categorization of design approach, thermal analysis,
Thermal degradation of two liquid fuels and detonation tests for pulse detonation engine studies
Shock Waves, 2006
The use of liquid fuels such as kerosene is of interest for the pulse detonation engine (PDE). Within this context, the aim of this work, which is a preliminary study, was to show the feasibility to initiate a detonation in air with liquid-fuel pyrolysis products, using energies and dimensions of test facility similars to those of PDEs. Therefore, two liquids fuels have been compared, JP10, which is a synthesis fuel generally used in the field of missile applications, and decane, which is one of the major components of standard kerosenes (F-34, Jet A1,. . .). The thermal degradation of these fuels was studied with two pyrolysis processes, a batch reactor and a flow reactor. The temperatures varied from 600 • C to 1,000 • C and residence times for the batch reactor and the flow reactor were, respectively, between 10-30 s and 0.1-2 s. Subsequently, the detonability of synthetic gaseous mixtures, which was a schematisation of the decomposition state after the pyrolysis process, has been studied. The detonability study, regarding nitrogen dilution and equivalence ratio, was investigated in a 50 mm-diameter, 2.5 m-long detonation tube. These dimensions are com-Communicated by S. Dorofeev.