Pressure and Thrust Measurements of a High-Frequency Pulsed-Detonation Tube (original) (raw)
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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.
Development of a Large Pulse Detonation Engine Demonstrator
47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2011
A test facility was designed and constructed to study pulse detonation engine (PDE) operations under a broad range of test parameters and to test and refine various subsystems and processes that are critical for a flight-weight PDE. The PDE combustor was designed to run on most common fuels, including kerosene, propane and hydrogen, with air or oxygen. A new ignition system was also built that features multiple low energy igniters located at the head manifold section of the engine, creating an impinging shock ignition when fired simultaneously. Instead of a separate initiator, an energetic mixture can be introduced in the ignition section to facilitate deflagration-to-detonation transition. The main sections of the combustor were fitted with fully enclosed water cooling passages. Kerosene fuel was preheated before mixing with preheated air in a mixing chamber. The fuel-air mixture and the purge air were injected into the engine at appropriate stages of the engine cycle using dual rotary valves, each having nine parallel ports. The fluid was injected into the combustor through ports located along the wall of the engine. The rotary valves were driven directly by a stepper motor. A pair of orifice plates were located downstream of the ignition zone for inducing deflagration-to-detonation transition. Dynamic pressure transducers and ion detectors were used for combustion diagnostics within the combustor. The various components of the engine were controlled via a data acquisition system, which was also used for monitoring the engine processes and for recording data.
Propulsive Performance of Airbreathing Pulse Detonation Engines
Journal of Propulsion and Power, 2006
The propulsive performance of airbreathing pulse detonation engines at selected flight conditions is evaluated by means of a combined analytical/numerical analysis. The work treats the conservation equations in axisymmetric coordinates and takes into account finite-rate chemistry and variable thermophysical properties for a stoichiometric hydrogen/air mixture. In addition, an analytical model accounting for the state changes of the working fluid in pulse detonation engine operation is established to predict the engine performance in an idealized situation. The system under consideration includes a supersonic inlet, an air manifold, a valve, a detonation tube, and a convergentdivergent nozzle. Both internal and external modes of valve operation are implemented. Detailed flow evolution is explored, and various performance loss mechanisms are identified and quantified. The influences of all known effects (such as valve operation timing, filling fraction of reactants, nozzle configuration, and flight condition) on the engine propulsive performance are investigated systematically. A performance map is established over the flight Mach number of 1.2-3.5. Results indicate that the pulse detonation engine outperforms ramjet engines for all the flight conditions considered herein. The benefits of pulse detonation engines are significant at low-supersonic conditions, but gradually decrease with increasing flight Mach number. Nomenclature A = preexponential factor A e = area of engine exit plane c = speed of sound c p = constant-pressure specific heat e t = specific total energy F = instantaneous thrust F sp = specific thrust
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...
Considerations and simulations about Pulse Detonation Engine
MATEC Web of Conferences, 2019
PDE propulsion can work from a subsonic regime to hypersonic regimes; this type of engine can have higher thermodynamic efficiency compared to other turbojet or turbofan engines due to the removal of rotating construction elements (compressors and turbines) that can reduce the mass and total cost of propulsion system. The PDE experimental researches focused on both the geometric configuration and the thermo-gas-dynamic flow aspects to prevent uncontrolled self-ignition. This article presents a series of numerical simulations on the functioning of PDE with hydrogen at supersonic regimens.
Toward a High-Frequency Pulsed-Detonation Actuator
44th AIAA Aerospace Sciences Meeting and Exhibit, 2006
This paper describes the continued development of an actuator, energized by pulsed detonations, that provides a pulsed jet suitable for flow control in high-speed applications. A high-speed valve, capable of delivering a pulsed stream of reactants-a mixture of H 2 and air-at rates of up to 1500 pulses per second, has been constructed. The reactants burn in a resonant tube and the products exit the tube as a pulsed jet. High frequency pressure transducers have been used to monitor the pressure fluctuations in the device at various reactant injection frequencies, including both resonant and off-resonant conditions. Pulsed detonations have been demonstrated in the λ/4 mode of an 8 inch long tube at ~600 Hz. The pulsed jet at the exit of the device has been observed using shadowgraph and an infrared camera.
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.
A pulsed detonation based multimode engine concept
AIAA paper, 2001
A novel multi-mode implementation of pulsed detonation engines is investigated in this paper. The various modes in this proposed concept are (as illustrated in Fig. [1]): (1) An ejector augmented pulse 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 of operation 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.