Thermodynamic Performance of Pulse Detonation Engine: A Technical Report (original) (raw)

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.

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.

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,

Innovative Trends in Pulse Detonation Engine, its Challenges and Suggested Solution

Journal of Basic and Applied Engineering Research, 2014

Pulse detonation engine (PDE) is an air-breathing intermittent combustion engine in which detonations are triggered at high frequencies through simultaneously burning and accelerating the fuel-air mixture. The generation shock waves are driven through a tube, creating a thrust. Shock Waves inside engine travels at either at subsonic or supersonic speed depending upon the physical parameters of tube, frequency of detonation and rate of injection of air-fuel mixture in the tube. Pulse detonation engine is getting considerable attention because of their superior performance parameters such as thermal efficiency and thrust/weight ratio over current traditional Rocket engine[1]. In this paper, the status of the theoretical and experimental study of Pulse Detonation Engine is presented. Secondly, a comparison of thermal efficiency of Pulse detonation Engine and generally used propulsion system (such as Rocket Engine) is studied and it is shown that efficiency of Pulse Detonation Engine is much higher. Also, the other advantages of Pulse Detonation Engine are discussed. Further, this paper presents a theoretical investigation of the problems preventing the widespread use of Pulse detonation Engine. In the end, a review of various methods which may overcome these challenges is provided, specifically, the approach of Detonation to Deflagration (DDT) method for solving Detonation Initiation problem is discussed in detail. The paper ends on a note of promising near future when Pulse Detonation Engines will become the staple for power generation and locomotion.

Examination of the Various Cycles for Pulse Detonation Engines

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2011

An examination of three common thermodynamic cycles developed for detonation-based engine analysis, namely the Humphrey, Fickett-Jacobs and Zel'dovich-von Neumann-Döring, shows that the last one is the most appropriate in capturing the essential physics in a one-dimensional framework. It is suggested that a local thermodynamic equilibrium assumption be invoked for the shock and heat release processes. An engineering approach to constructing the ZND cycle and the need for precompression are addressed.

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.

Analytical Estimation of Performance Parameters of an Ideal Pulse Detonation Engine

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2003

The cycle of an ideal pulse detonation engine (PDE) was theoretically analyzed. A PDE was modeled as a straight tube, one end of which was closed and the other end open. A detonation wave was ignited at the closed end and simultaneously started to propagate toward the open end. When the detonation wave broke out from the open end, a rarefaction wave started to propagate from the open end toward the closed end. We analytically obtained a functional form of the thrust-density history, showing a plateau followed by decay. Using the obtained history of the thrust density, we formulated some PDE performance parameters such as impulse density per cycle.

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].

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.