Oxygen concentration distribution in a pulse detonation engine with nozzle–ejector combinational structures

2021 ◽  
pp. 095441002199128
Author(s):  
Zhiwu Wang ◽  
Lisi Wei ◽  
Weifeng Qin ◽  
Zijian Liang ◽  
Kun Zhang
Keyword(s):  
Oxygen Concentration ◽  
Concentration Distribution ◽  
Axial Direction ◽  
Time Range ◽  
Convergent Nozzle ◽  
Pulse Detonation Engines ◽  
Pulse Detonation ◽  
Different Types ◽  
Detonation Engine ◽  
Ejection Speed

Pulse detonation engines (PDEs) with three different types of nozzle–straight ejector combinational structures at three different ejector positions were simulated by the unsteady 2-D axisymmetric method to understand the influence of nozzle–ejector combinational structures on the performance of PDEs. Three types of nozzles included the straight nozzle, convergent nozzle, and convergent–divergent (CD) nozzle. Three ejector positions were considered according to the ratio of the distance between the nozzle outlet and the ejector inlet to the diameter of PDEs (Δx/d). Propane was used as the fuel and air as the oxidizer. The simulation results indicated that for the PDE with the straight nozzle, it took the shortest time for high-temperature burnt gas to exhaust from the detonation tube. For the PDE with the CD nozzle, the time at which the ejector was filled with external air was the fastest. Within the time range of t = 0–10 ms, the ejected air was less than the original air in the ejector among all the nine combinational structures. The maximum ejected air was obtained with the convergent nozzle, followed by the CD nozzle, and the minimum with the straight nozzle. For certain nozzles, the maximum air was ejected at the ejector position of Δx/d = +1, followed by the ejector position of Δx/d = 0, and the minimum at the ejector position of Δx/d = −1. For the convergent nozzle–ejector combinational structure, the air ejection speed was the fastest. Oxygen concentration distribution in the PDE with the CD nozzle was more uniform along the axial direction than the other nozzles.

scholarly journals Review on Recent Advances in Pulse Detonation Engines

2016 ◽  
Vol 2016 ◽  
pp. 1-16 ◽  
Author(s):  
K. M. Pandey ◽  
Pinku Debnath
Keyword(s):  
Detonation Wave ◽  
Combustion Process ◽  
Experimental Studies ◽  
Pulse Detonation Engine ◽  
Wave Flow ◽  
Pulse Detonation Engines ◽  
Pulse Detonation ◽  
Propulsion Performance ◽  
Detonation Tube ◽  
Detonation Engine

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.

Forced Oscillations in a Mixed-Compression Inlet at Mach 3.5 for Pulse Detonation Engine Systems

2005 ◽  
Vol 128 (3) ◽  
pp. 494-506 ◽  
Author(s):  
Venkata Nori ◽  
Nelson Lerma ◽  
Jonas Gustavsson ◽  
Corin Segal ◽  
Rene Fernandez
Keyword(s):  
Forced Oscillations ◽  
Pulse Detonation Engines ◽  
Pulse Detonation ◽  
Large Pressure ◽  
Detonation Engine ◽  
Flow Oscillations ◽  
Large Injection ◽  
Inlet Unstart ◽  
Pressure Perturbations ◽  
Engine Systems

The effects of oscillatory backpressure on the air induction system for pulse detonation engines were examined for a two-dimensional, mixed-compression configuration at a freestream Mach number of 3.5. The pressure perturbations at the diffuser exit were produced by injecting air through four ports located at the corners of the exit cross section. The frequency, coupling of the ports and airflow rates through the ports were varied, simulating the operation of detonation tubes. A terminal normal shock in the diffuser oscillated in the excited inlet, causing large pressure fluctuation amplitudes at some locations. Large injection mass flows resulted in inlet flow oscillations throughout the inlet, increased the spillage, yet did not cause inlet unstart.

Analysis on impulse characteristics of pulse detonation engine with nozzles

2021 ◽  
Vol 0 (0) ◽  
Author(s):  
Xiao-long Huang ◽  
Ning Li ◽  
Yang Kang ◽  
Hui Wang ◽  
Chun-sheng Weng
Keyword(s):  
Dynamic Pressure ◽  
Tunable Diode Laser ◽  
Pulse Detonation Engine ◽  
Two Phase ◽  
Convergent Nozzle ◽  
Pulse Detonation ◽  
Laser Absorption ◽  
Propulsion Performance ◽  
Detonation Engine ◽  
Impulse Characteristics

Abstract In order to study the influence of different nozzle configurations on the gas–liquid two-phase pulse detonation engine (PDE) propulsion performance, the measurement system based on the tunable diode laser absorption spectroscopy (TDLAS) technology is built to measure the velocity and the temperature, while the high frequency dynamic pressure sensor is used to measure the nozzle gas pressure. Based on the momentum principle, the contribution mechanism of unsteady gas jet on thrust is obtained indirectly by TDLAS data. The results show that the impulses of PDE with non-nozzle, convergent nozzle, divergent nozzle and convergent–divergent nozzle are 1.95, 2.08, 1.85 and 2.16 N∙s within 20 ms of the exhaust period, respectively. The analysis reveals that the impulses of PDE with convergent and convergent–divergent nozzles are larger than that with non-nozzle, while the impulse of PDE with divergent nozzle is smaller than that with non-nozzle. The research results in this paper can provide reference for the design of nozzles for PDE.

scholarly journals Study on Influence of Diameter on Detonation Acoustic Characteristics of Pulse Detonation Engine

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Gui-yang Xu ◽  
Chun-guang Wang ◽  
Yan-fang Zhu ◽  
Hong-yan Li ◽  
Lun-kun Gong ◽  
...  
Keyword(s):  
Acoustic Characteristic ◽  
Pulse Detonation Engine ◽  
Acoustic Characteristics ◽  
Experiment System ◽  
Pulse Detonation ◽  
Impact Noise ◽  
Maximum Duration ◽  
Detonation Engine ◽  
Set Up ◽  
Different Diameters

AbstractThe experiment system of pulse detonation engine is set up to investigate on influence of diameter on detonation acoustic characteristic. The research of detonation acoustic characteristic of pulse detonation engine for four different diameters in different angles is carried out. Results from the test show that as the PDE diameter increasing, there are increases in amplitudes of impact noise in all angles, and the growth rate of amplitude of impact noise in the 90° direction is generally greater than that in the 0° direction. The smaller PDE diameter is, the distance of most obvious directivity at 0° turning to most obvious directivity at 30° is shorter. When the distance is shorter, such as 200 mm, the duration of detonation acoustic is increasing with the increase of PDE diameter, however, when the distance is longer, such as 3000 mm, it is just the opposite. The maximum duration of detonation acoustic is appeared in 3000 mm under 30 mm PDE diameter which reaches to 1.44 ms.

Experimental investigations of momentum and heat transfer in pulse detonation engines

2002 ◽  
Vol 29 (2) ◽  
pp. 2847-2854 ◽  
Author(s):  
Jiro Kasahara ◽  
Kouki Takazawa ◽  
Takakage Arai ◽  
Yu Tanahashi ◽  
Shingo Chiba ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Experimental Investigations ◽  
Pulse Detonation Engines ◽  
Pulse Detonation ◽  
Momentum And Heat Transfer
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