scholarly journals Numerical simulation and performances evaluation of the pulse detonation engine

2018 ◽  
Vol 234 ◽  
pp. 01001 ◽  
Author(s):  
Vasile Prisacariu ◽  
Constantin Rotaru ◽  
Ionică Cîrciu ◽  
Mihai Niculescu
Keyword(s):  
Numerical Simulation ◽  
High Speed ◽  
Unmanned Vehicles ◽  
Working Fluid ◽  
Detonation Waves ◽  
Pulse Detonation Engine ◽  
Space Vehicles ◽  
Propulsion Systems ◽  
Pulse Detonation ◽  
Detonation Engine

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.

scholarly journals Technological advancements in Pulse Detonation Engine Technology in the recent past: A Characterized Report

2019 ◽  
Vol 11 (4) ◽  
pp. 81-92
Author(s):  
Bharat Ankur DOGRA ◽  
Mehakveer SINGH ◽  
Tejinder Kumar JINDAL ◽  
Subhash CHANDER
Keyword(s):  
High Speed ◽  
Combustion Process ◽  
Detonation Waves ◽  
Status Report ◽  
Pulse Detonation Engine ◽  
Operating Cycle ◽  
Air Breathing ◽  
Pulse Detonation ◽  
Pulsed Detonation ◽  
Detonation Engine

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-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 paper is the extension of the previous study which is also a well characterized status report of PDE in different areas. The present study deals with the categorization of the design approach, computations & simulations, flow visualization, DDT & Thrust enhancement, PDRE’s, experimental detonation engines with some of the experience and research undertaken in Punjab Engineering College under the complete supervision and guidance of Prof. Tejinder Kumar Jindal followed by applications of PDE technology.

Energy and Exergy Analyses of the Pulse Detonation Engine

2003 ◽  
Vol 125 (4) ◽  
pp. 1075-1080 ◽  
Author(s):  
T. E. Hutchins ◽  
M. Metghalchi
Keyword(s):  
Gas Turbine ◽  
Constant Volume ◽  
Supersonic Combustion ◽  
Working Fluid ◽  
Pulse Detonation Engine ◽  
Pulse Detonation ◽  
Energy And Exergy ◽  
Efficiency And Effectiveness ◽  
Detonation Engine ◽  
Exergy Analyses

Energy and exergy analyses have been performed on a pulse detonation engine. A pulse detonation engine is a promising new engine, which uses a detonation wave instead of a deflagration wave for the combustion process. The high-speed supersonic combustion wave reduces overall combustion duration resulting in an nearly constant volume energy release process compared to the constant pressure process of gas turbine engines. Gas mixture in a pulse detonation engine has been modeled to execute the Humphrey cycle. The cycle includes four processes: isentropic compression, constant volume combustion, isentropic expansion, and isobaric compression. Working fluid is a fuel-air mixture for unburned gases and products of combustion for burned gases. Different fuels such as methane and JP10 have been used. It is assumed that burned gases are in chemical equilibrium states. Both thermal efficiency and effectiveness (exergetic efficiency) have been calculated for the pulse detonation engine and simple gas turbine engine. Comparison shows that for the same pressure ratio pulse detonation engine has better efficiency and effectiveness than the gas turbine system.

scholarly journals Numerical simulation of the nozzle and ejector effect on the performance of a pulse detonation engine

2018 ◽  
Vol 22 (3) ◽  
pp. 1227-1237 ◽  
Author(s):  
Zhiwu Wang ◽  
Xing Liu ◽  
Yaqi Wang ◽  
Hongwei Li ◽  
Kun Zhang ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Pulse Detonation Engine ◽  
Pulse Detonation ◽  
Detonation Engine

Energy and Exergy Analyses of the Pulse Detonation Engine

2001 ◽  
Author(s):  
Timothy E. Hutchins ◽  
Mohamad Metghalchi
Keyword(s):  
Gas Turbine ◽  
Constant Volume ◽  
Supersonic Combustion ◽  
Working Fluid ◽  
Pulse Detonation Engine ◽  
Pulse Detonation ◽  
Energy And Exergy ◽  
Efficiency And Effectiveness ◽  
Detonation Engine ◽  
Exergy Analyses

Abstract Energy and exergy analyses have been performed on a pulse detonation engine. A pulse detonation engine is a promising new engine, which uses a detonation wave instead of a deflagration wave for the combustion process. The high-speed supersonic combustion wave reduces overall combustion duration resulting in a nearly constant volume energy release process compared to the constant pressure process of gas turbine engines. Gas mixture in a pulse detonation engine has been modeled to execute the Humphrey cycle. The cycle includes four processes: isentropic compression, constant volume combustion, isentropic expansion and isobaric compression. Working fluid is a fuel-air mixture for unburned gases and products of combustion for burned gases. Different fuels such as methane and JP10 have been used. It is assumed that burned gases are in chemical equilibrium states. Both thermal efficiency and effectiveness (exergetic efficiency) have been calculated for the pulse detonation engine and simple gas turbine engine. Comparison shows that for the same pressure ratio pulse detonation engine has better efficiency and effectiveness than the gas turbine system.

Thrust Augmentation of Single Cycle Pulse Detonation Engine using Nozzles

2021 ◽  
Vol 13 (1) ◽  
Author(s):  
Sanjeevkumar Dhama ◽  
T.K. Jindald ◽  
S.K. Mangal
Keyword(s):  
Cost Effective ◽  
Area Ratio ◽  
Thermodynamic Efficiency ◽  
Pulse Detonation Engine ◽  
Propulsion Systems ◽  
Pulse Detonation ◽  
Detonation Engine ◽  
Varying Length ◽  
Shaped Nozzle ◽  
Divergent Angle

Pulse detonation propulsion systems have the potential to provide better performance with additional advantages such as considerably light in weight, cost effective and reduced complexity in comparison with other propulsion systems which are currently in use. These improvements are due to the high thermodynamic efficiency obtained because of constant-volume combustion. Pulse detonation cycle can be used for both air-breathing and rocket based systems. Present study investigates the effect of nozzles in various configurations. They are straight nozzle, conical and bell-shaped nozzles with varying length, divergent angles and area ratios on the thrust augmentation of Pulse Detonation Engine (PDE) test rig which was developed by research team at Punjab Engg. College (PEC), Chandigarh. It was found from the experiments that the conical nozzle with high divergent angle of 20° and high nozzle area ratio of around 23 increased the thrust to 14%. The bell shaped nozzle, with 20° angle of divergence and a nozzle area ratio of just around 7, produced 59.5% more thrust in comparison with baseline engine. The augmentation in thrust was found to be as high as 55% in comparison with straight nozzle. Divergent nozzles produced negative thrust with less divergent angle but gave an increment of 11.28% with high angle of divergence in comparison with a straight nozzle.

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