scholarly journals Influence of Nozzle Type, Divergence Angle and Area Ratio on Impulse of Pulse Detonation Engine

2020 ◽  
Vol 12 (2) ◽  
pp. 35-45
Author(s):  
Sanjeev Kumar DHAMA ◽  
T. K. JINDAL ◽  
S. K. MANGAL
Keyword(s):  
Area Ratio ◽  
Divergence Angle ◽  
Nozzle Geometry ◽  
Oxygen Mixture ◽  
Pulse Detonation Engine ◽  
Pulse Detonation ◽  
Detonation Engine ◽  
Shaped Nozzle ◽  
Divergent Angle ◽  
Thrust Stand

The influence of nozzle geometry on the impulse produced by the single cycle Pulse detonation engine (PDE) was experimentally investigated. For each experiment the nozzles were attached at the end of the engine. The impulse produced by the pulse detonation engine was calculated from the measured thrust. The thrust measurement was done by sliding the engine on the central bar of the thrust stand. The main structure of the basic PDE has a detonation tube with one terminal closed, a Schelkin spiral used as deflagration to detonation device, and a thrust stand to support the structure. Stoichiometric acetylene and oxygen mixture were used as detonation mixture. Various nozzles with a range of divergent angle and area ratios were tested. The calculations of the impulse were made from the thrust pulse for the duration it lasted. The effect of the type of nozzle, divergent angle and area ratio were observed. The bell shaped nozzle with large angle of divergence produced maximum specific impulse of 80 Sec with 20° divergence angle and area ratio of 6.942; maximum impulse was produced by the bell shaped nozzle with a small area ratio of 2.969 and 10° divergence angle. The maximum total impulse obtained was 1200 N-sec.

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.

scholarly journals Analysis of Equivalence Ratio in an Oxygen Acetylene Mixture

2019 ◽  
Vol 11 (4) ◽  
pp. 171-177
Author(s):  
SHIVAM ◽  
Mehakveer SINGH ◽  
Bharat Ankur DOGRA ◽  
Subhash CHANDER ◽  
T. K. JINDAL
Keyword(s):  
Mass Flow ◽  
Equivalence Ratio ◽  
Oxygen Mixture ◽  
Settling Chamber ◽  
Pulse Detonation Engine ◽  
Filling Fraction ◽  
Pulse Detonation ◽  
Feasible Range ◽  
Detonation Engine ◽  
Valve Opening

The paper presents an exclusive approach to analyze the oxygen and acetylene mixture in a Pulse Detonation Engine setup at PEC. The experiment was carried out by varying the amount of mass flow of acetylene and oxygen into the tube at different pressures in the settling chamber. The equivalence ratio of the acetylene-oxygen mixture with respect to the valve opening time of acetylene and oxygen was plotted. The analysis of equivalence ratio also defines the procedure which involved the cycle of valves and pressure supply to attain different values of filling fraction of the tube. The results experimentally predicted the feasible range of operation at different pressures in the settling chamber of the pulse detonation engine.

Propulsive Performance of Ideal Detonation Turbine Based Combined Cycle Engine

2012 ◽  
Vol 134 (8) ◽  
Author(s):  
Hua Qiu ◽  
Cha Xiong ◽  
Chuan-jun Yan ◽  
Wei Fan
Keyword(s):  
Pressure Ratio ◽  
Area Ratio ◽  
Combined Cycle ◽  
Performance Model ◽  
Propulsion System ◽  
Pulse Detonation Engine ◽  
Inlet Temperature ◽  
Pulse Detonation ◽  
Propulsive Performance ◽  
Detonation Engine

A novel two-mode propulsion system based on detonation combustion, known as a detonation turbine based combined cycle engine (DTBCC), was proposed and thermodynamically analyzed for potential application to aircrafts whose flight Mach number is from 0 to 5. The obvious advantage of the two-mode system is that both modes share the same multidetonation chambers. The quasi-stable total temperature and total pressure for inlet conditions of the turbine could be realized in this hybrid pulse detonation engine. A key parameter (drive area ratio) was defined as the ratio of the outflow area at the head to the cross-sectional area of the detonation chamber. The calculated results showed that the increase of the drive area ratio led to the increase in the mass flow entering the turbine; however, this led to the decrease of the total inlet temperature, the total inlet pressure, and the expansion-pressure ratio of the turbine. Compared with an ideal turbojet engine, the inlet temperature of the turbine in a preturbine hybrid pulse detonation engine with a drive area ratio of 1 was 80 K lower than the former under the same pressure ratio and the same fuel-air ratio. In other words, the increase of the drive area ratio may improve the performance of this hybrid pulse detonation engine. Variation of the pressure ratio was adapted to varied flight Mach numbers by a change of the drive area ratio, which induced the enlargement of the operating range. Finally, a performance model was established to research the components’ characteristics and the propulsive performance of the engine. Preliminary performance estimates suggested that thrust and specific fuel consumption of the two-mode propulsion system were superior to the existing turbine based combined cycle designs.

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.

An analytical model for the impulse of a single-cycle pulse detonation engine

2001 ◽  
Author(s):  
E. Wintenberger ◽  
J. Austin ◽  
M. Cooper ◽  
S. Jackson ◽  
J. Shepherd
Keyword(s):  
Analytical Model ◽  
Pulse Detonation Engine ◽  
Single Cycle ◽  
Pulse Detonation ◽  
Detonation Engine ◽  
Cycle Pulse
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