Abstract
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.
Highlights
According to scientific literature [1,2,3,4] there has been preoccupation, since 1940, with propulsion systems based on detonation, which presupposes the elimination of at least the rotating constructive elements placed after the combustion chamber
The combustion mixture is ignited in an open chamber, the resulting combustion increases the mixture pressure to about 10 MPa, which expands into a nozzle at thousands of meters per second, which can be numerically modelled as a constant volume combustion process, where more chemical energy is released as heat than the constant pressure process found in conventional turbine engines
Assuming pulse detonation engine (PDE) with a combustion chamber of an jet engine, we can define a series of general requirements that can characterize such a propulsion system, [14, 15]: ensure a stable combustion process; the efficiency of the combustion process is the highest possible with the least possible total and static pressure losses; have a low thermal load and a high operating resource; have a reduced dimensioning with positive implications for the mass and mechanical strength
Summary
According to scientific literature [1,2,3,4] there has been preoccupation, since 1940, with propulsion systems based on detonation, which presupposes the elimination of at least the rotating constructive elements placed after the combustion chamber (turbine). The concept of PDE operation is similar to the impulse jet engine, but the difference is the combustion rate of the fuel mixture and the oxidant (deflection versus detonation). Experimental tests have encountered a number of difficulties regarding both the transition of subsonic deflagration into a supersonic detonation wave and the correct mixing of the fuel and the oxidant to result in uniform detonation. PDE uses the detonation waves for combustion of the fuel and oxidant mixture; theoretically, this type of engine can operate from a subsonic regime to hypersonic regimes (Mach> 5), [1,2,3,4,5]. Elimination of the turbine makes it possible to increase the temperature and speed of combustion gases through a more efficient supersonic combustion (detonation) and is capable of providing gas velocities and pressures far superior to conventional combustion (deflagration). Scientific references indicate the PDE classification by design type: pure (PDE with / without pre-dielectric, with / without ejector, single tube PDE, multi-tube PDE, PDE-turbojet PDE-rocket) of the fuel used [11, 12]
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