Experimental Parametric optimization, Detonation Behaviour study of Pulse Detonation Engine
| PI Details | Co-PI Details |
|---|---|
|
Dr T K Jindal
Designation: Professor |
| Funding Agency | Project Cost |
|---|---|
| Aeronautical Research and Development Board, DRDO, New Delhi |
Rs. 29.10 Lakh |
| Start Date | Completion Date | Status |
|---|---|---|
| 2017-06-16 | 2020-03-31 | Completed |
Abstract
The project form ARDB was undertaken for analysis and optimization of pulse detonation engine parameters experimentally. The combustion tube length, diameter, Schelkin spiral dimensions were optimized for maximum thrust obtained from the PDE. Flow control and fire control systems were developed and used for the purpose. The installation of PDE as a sustainer in a missile was also undertaken and found that it can be integrated.
| Manpower Sanctioned/Hired | Manpower Trained |
|---|---|
|
RA (Nos): 01 |
Ph.D Produced: 2 |
Equipment Sanctioned/Procured
|
Name of Equipment |
Make & Model |
Year of Purchase |
Cost |
Salient Features of Equipment |
Condition (Working /Not Working) |
|---|---|---|---|---|---|
|
National Instrument Data Acquisition system |
|
|
15.00 Lakh |
Data Acquisition @ 1 MHz |
Working |
|
PDE test Rig |
|
|
2.00 Lakh |
Test Rig |
Working |
Publications
List of SCI Publications under Project
|
Authors Name |
Title of Paper |
Journal Name |
Volume |
No. |
Page No. |
Year |
DOI Number |
|---|---|---|---|---|---|---|---|
|
B A Dogra |
A Characterized Status Report on Pulse Detonation Engine |
INCAS Bulletin |
11 |
2 |
69-83 |
2019 |
|
|
B A Dogra |
Technological advancements in Pulse Detonation Engine Technology in the recent past: A Characterized Report |
INCAS Bulletin |
11 |
4 |
81-92 |
2019 |
|
|
B A Dogra |
Analysis of Equivalence Ratio in an Oxygen Acetylene Mixture
|
INCAS Bulletin |
11 |
4 |
171-177 |
2019 |
10.13111/2066-8201.2019.11.4.15 |
|
S Dhama |
Thrust Augmentation of Single Cycle Pulse Detonation Engine using Nozzles |
Int. J. Vehicle Structures & Systems |
13 |
1 |
80-85 |
2021 |
|
|
S Dhama |
Influence of Nozzle Type, Divergence Angle and Area Ratio on Impulse of Pulse Detonation Engine |
INCAS Bulletin |
12 |
2 |
35-45 |
2020 |
10.13111/2066-8201.2020.12.2.4 |
|
T K Jindal |
Proposed thrust profile design of Pulse Detonation Engine for Aerospace Applications |
Springer, Advances in Energy and Combustion, 2021 |
-- |
-- |
85-102 |
2021 |
10.1007/978-981-16-2648-7_4 |
|
Udit Vohra, Rajpreet Singh, Vinayak Bassi, T. K. Jindal, and Amarjit Singh |
Numerical Study of Deflagration to Detonation Transition in 2D and Axisymmetric Detonation Tube with Obstacles Using OpenFOAM
|
-- |
-- |
807-820 |
2021 |
10.1007/978-981-15-5996-9_62 |
Output/Outcome of the Project
Output/Outcome of the project
The parameters of the combustor of PDE have been optimized for maximum thrust from the engine. The PDE system has been analyzed to be eligible for missile propulsion system as sustainer. Flow control system and fire control systems have been developed. The test rig has been tested for a frequency of 20 Hz.