The Thermodynamic Performance of Ideal Single-Tube Air-Breathing Pulse Detonation Engine

2006 ◽  
Author(s):  
Hua Qiu ◽  
Cha Xiong ◽  
Chuan-jun Yan
Keyword(s):  
Pulse Detonation Engine ◽  
Air Breathing ◽  
Single Tube ◽  
Pulse Detonation ◽  
Thermodynamic Performance ◽  
Detonation Engine

The Thermodynamic Performance of Ideal Single-Tube Air-Breathing Pulse Detonation Engine

2006 ◽  
Author(s):  
Hua Qiu ◽  
Cha Xiong ◽  
Chuan-Jun Yan
Keyword(s):  
Operation Mode ◽  
Equal Mass ◽  
Pulse Detonation Engine ◽  
Air Breathing ◽  
Single Tube ◽  
Pulse Detonation ◽  
Detonation Engine ◽  
Purge Gas ◽  
Operation Cycle ◽  
Factor Α

A new single-tube air-breathing pulse detonation engine (APDE) with bypass air duct is introduced. It is composed of inlet, valve, detonation chamber, bypass air duct and nozzle. Based on the analysis of the operation cycle of the APDE, airstreams flowing into the engine can be separated into three parts: one is flowing out from the engine through the bypass; one is exhausted from the nozzle as purge gas; and the else is mixed with fuel and is combusted. And the concept of cycle factor α that represents the ratio of air quantity for detonation combustion to incoming air quantity is defined to analyze the influence of the mass distribution on the performance of APDE. Although α has no effect on the cycle thermal efficiency of APDE, it influences the engine propulsive performance. When the APDE is full fuel filled and with the equivalent incoming air-flow and fuel-flow rate, the APDE will be superior to ramjet for 0∼5 Mach if α is larger than 0.8. When the APDE and ramjet work with equal mass fuel-air ratio of combustion, the specific fuel consumption of APDE is lower than that of ramjet for 0∼5 Mach. Also, if a is higher than 0.9, the specific thrust of APDE is higher than ramjet for 0∼5 Mach. Further, the operation mode of partial fuel filling can be used to enhance the performance, but it simultaneously decreases the total thermal cycle efficiency.

Air-Breathing Liquid-Fueled Pulse Detonation Engine Demonstrator

2005 ◽  
Vol 402 (4-6) ◽  
pp. 93-95 ◽  
Author(s):  
S. M. Frolov ◽  
V. S. Aksenov ◽  
V. Ya. Basevich
Keyword(s):  
Pulse Detonation Engine ◽  
Air Breathing ◽  
Pulse Detonation ◽  
Detonation Engine

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.

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