In pulse detonation engines (PDE), combustion temperatures can rise as high as 3000 K across the detonation wave. The continuous exposure to such elevated temperature may risk the integrity of the structural components of the engines. In order to be able to estimate the heat load accurately. Hence, numerical and experimental studies of the temperature distribution on a pulse detonation engine model was conducted to quantify the heat load. Navier-Stokes conservation equations with viscosity and chemical reaction for deflagration-to-detonation transition (DDT) in detonation engines were solved through computational fluid dynamics. Reactive flow field of premixed mixtures (propane-oxygen) was modeled for detonation process. In the simulation, short-term detonation combustion (ms) and long-term wall heating process(s) are carried out together. Both single detonation and multiple continuous detonations were simulated and tested, and the simulation results are consistent with the experimental results. The results show that there is a correlation between heat flux and detonation wave structure and the instantaneous maximum heat flux appears in the detonation wave region of the detonation tube wall. The distribution of transient heat flux in time and space is very uneven, and the difference between transient heat flux and average heat flux is large. The position of detonation wave formation is the turning point of PDE wall temperature, and the temperature at the front end of the turning point is lower than that at the back end. The results show that the fresh mixtures have cooling effect on the detonation tube wall, which leads to the increase of the inner wall temperature with oscillation and the continuous increase of the outside wall temperature. The maximum wall temperature and the speed of temperature rise are positively correlated with detonation frequency. The results also show that the heat transfer coefficient of detonation tube has an effect on the initiation of detonation wave. When the heat transfer coefficient is large, detonation wave can not initiate in the studied engine. The focus of thermal protection is different between single detonation and multiple continuous detonations. Heat management of the detonation engines highlights an important part on the engine construction.
| Published in | International Journal of Fluid Mechanics & Thermal Sciences (Volume 8, Issue 2) |
| DOI | 10.11648/j.ijfmts.20220802.12 |
| Page(s) | 34-40 |
| Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
| Copyright |
Copyright © The Author(s), 2022. Published by Science Publishing Group |
Pulse Detonation Engines, Deflagration-to-Detonation Transition, Heat Flux, Single Detonation, Multiple Continuous Detonations
| [1] | Noor Alam; K. K. Sharma; K. M. Pandey. Numerical investigation of flame propagation in pulse detonation engine with variation of obstacle clearance, [J] Journal of Thermal Analysis and Calorimetry 2020, 140 (3): 2485-2495. |
| [2] | Yan-fang Zhu; Gui-yang Xu; Chun-guang Wang. Study on Acoustic Detection of the Working State of Pulse Detonation Engine. [J] International Journal of Turbo & Jet Engines. 2020, 37 (1): 71-78. |
| [3] | N. Alam; K. M. Pandey; K. K. Sharma. Numerical Investigation of Combustion Wave Propagation in Obstructed Channel of Pulse Detonation Engine using Kerosene and Butane Fuels. [J] Journal of Applied Fluid Mechanics 2019, 12 (3): 883-890. |
| [4] | Vasile Prisacariu; Constantin Rotaru; Ionică Cîrciu. Numerical simulation and performances evaluation of the pulse detonation engine. [J] MATEC Web of Conferences, 2018, 234 (15): 365-375. |
| [5] | Jin Jie, Liu Daxiang. Numerical simulation of three-dimension combustion in an annular combustor during a transient state [J]. Journal of Aerospace Power, 2010, 25 (02): 314-319. |
| [6] | Wu Dan, Wang Jianping. Influences of viscosity and thermal conductivity on detonation waves [J]. Journal of applied mechanics, 2012, 29 (06): 630-635. |
| [7] | Chen Wenjuan, Zhang Qun, Fan Wei. Experiment on wall temperature of an air-breathing pulse detonation engine [J]. Propulsion technology, 2017, 32 (02): 296-300. |
| [8] | Zheng Longxi, Yan Chuanjun, Fan Wei. Experimental Investigation on Outer Wall Temperature Distribution of a Pulse Detonation Engine Model [J]. Combustion science and technology, 2019 (04): 344-347. |
| [9] | Jianling Li, Wei Fan, Chuanjun Yan, et al. Experimental Investigations on Detonation Initiation in a Kerosene-Oxygen Pulse Detonation Rocket Engine [J]. Combustion Science and Technology, 2015, 181 (1): 417-432. |
| [10] | Shchelkin K I. Some Methods for Control of Detonation [J]. Soviet Journal of Technical Physics, 1990, 10 (2): 832-827. |
| [11] | Peraldi O, Knystautas R, Lee J H. Criteria for Transition to Detonation in Tubes [c]//Symposium (International) on Combustion. Elsevier, 2010, 21 (1): 1629-1637. |
| [12] | Theuerkauf, S., Schauer, F., Anthony, R., Paxson, D., Stevens, C., and Hoke, J., “Comparison of Simultated and Measured Instantaneous Heat Flux in a Rotating Detonation Engine”, 54th AIAA Aerospace Sciences Meeting. AIAA 2016-1200, San Diego, CA, 2016. |
| [13] | Meyer, S. J., Polanka, M. D., Schauer, F. R., Anthony, R. J., Stevens, C., Hoke, J. L., and Rein, K., “Experimental Characterization of Heat Transfer Coefficients in a Rotating Detonation Engine,” 55th AIAA Aerospace Sciences Meeting, AIAA 2017-1285, Grapevine, TX, 2017. |
| [14] | Gamezo V N, Ogawa T, Oran E S Deflagration-to-Detonation Transition in Premixed H2-Air in Channels With Obstacles [C] // 45th AIAA Aerospace Sciences Meeting, Reno, NV. 2007. |
| [15] | Gamezo V N, Ogawa T, Oran E S Deflagration-to-Detonation Transition in H2-Air Mixtures: Effect of Blockage Ratio [C]. AIAA 2009-440.2009. |
| [16] | Ettner, F., 2013. Effiziente numerische Simulation des Deflagrations Detonations bergangs. PhD Dissertation, TU Munchen, Munich. |
| [17] | Olcucuoglu, B., 2016. Detailed Heat Transfer Analysis of Detonation Engines. Short Training Programme Report, von Karman Institute for Fluid Dynamics, Rhode-Saint-Genese. |
| [18] | Qiaofeng Xie. A preliminary heat transfer analysis of pulse detonation engines. [J]Transportation Research Procedia 2018, 29 (3): 279-288. |
| [19] | Jishuang Gong; Hu Ma; Qiaofeng Xie. Experimental Study on Pulse Detonation Engine with Two-Phase Inhomogeneous Mixture. [J]International Journal of Aerospace Engineering Volume 2020, 33 (02): 313-316. |
| [20] | Arnab Roy, peter strakey, Todd Sidwell. Unsteady Heat Transfer Analysis to predict Combustor Wall Temperature in Rotating Detonation Engine [C]. AIAA, 2015-51, 2015. |
| [21] | Zhou Xudong, Fan Wei. et al. the position of detonation wave formation in pulse detonation rocket engine is determined by wall temperature [J]. Journal of Propulsion Technology, 2012, 33 (02): 313-316. |
| [22] | Berke Olcucuoglu; Bayindir H. Saracoglu. A preliminary heat transfer analysis of pulse detonation engines. [J]Transportation Research Procedia, 2018, 29 (1): 279-288. |
APA Style
Wang Qingwu. (2022). Temperature Distribution Analysis of Pulse Detonation Engines. International Journal of Fluid Mechanics & Thermal Sciences, 8(2), 34-40. https://doi.org/10.11648/j.ijfmts.20220802.12
ACS Style
Wang Qingwu. Temperature Distribution Analysis of Pulse Detonation Engines. Int. J. Fluid Mech. Therm. Sci. 2022, 8(2), 34-40. doi: 10.11648/j.ijfmts.20220802.12
AMA Style
Wang Qingwu. Temperature Distribution Analysis of Pulse Detonation Engines. Int J Fluid Mech Therm Sci. 2022;8(2):34-40. doi: 10.11648/j.ijfmts.20220802.12
Share This Article
Twitter
Linked In
Facebook
Copy
Download@article{10.11648/j.ijfmts.20220802.12,
author = {Wang Qingwu},
title = {Temperature Distribution Analysis of Pulse Detonation Engines},
journal = {International Journal of Fluid Mechanics & Thermal Sciences},
volume = {8},
number = {2},
pages = {34-40},
doi = {10.11648/j.ijfmts.20220802.12},
url = {https://doi.org/10.11648/j.ijfmts.20220802.12},
eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijfmts.20220802.12},
abstract = {In pulse detonation engines (PDE), combustion temperatures can rise as high as 3000 K across the detonation wave. The continuous exposure to such elevated temperature may risk the integrity of the structural components of the engines. In order to be able to estimate the heat load accurately. Hence, numerical and experimental studies of the temperature distribution on a pulse detonation engine model was conducted to quantify the heat load. Navier-Stokes conservation equations with viscosity and chemical reaction for deflagration-to-detonation transition (DDT) in detonation engines were solved through computational fluid dynamics. Reactive flow field of premixed mixtures (propane-oxygen) was modeled for detonation process. In the simulation, short-term detonation combustion (ms) and long-term wall heating process(s) are carried out together. Both single detonation and multiple continuous detonations were simulated and tested, and the simulation results are consistent with the experimental results. The results show that there is a correlation between heat flux and detonation wave structure and the instantaneous maximum heat flux appears in the detonation wave region of the detonation tube wall. The distribution of transient heat flux in time and space is very uneven, and the difference between transient heat flux and average heat flux is large. The position of detonation wave formation is the turning point of PDE wall temperature, and the temperature at the front end of the turning point is lower than that at the back end. The results show that the fresh mixtures have cooling effect on the detonation tube wall, which leads to the increase of the inner wall temperature with oscillation and the continuous increase of the outside wall temperature. The maximum wall temperature and the speed of temperature rise are positively correlated with detonation frequency. The results also show that the heat transfer coefficient of detonation tube has an effect on the initiation of detonation wave. When the heat transfer coefficient is large, detonation wave can not initiate in the studied engine. The focus of thermal protection is different between single detonation and multiple continuous detonations. Heat management of the detonation engines highlights an important part on the engine construction.},
year = {2022}
}
TY - JOUR T1 - Temperature Distribution Analysis of Pulse Detonation Engines AU - Wang Qingwu Y1 - 2022/07/13 PY - 2022 N1 - https://doi.org/10.11648/j.ijfmts.20220802.12 DO - 10.11648/j.ijfmts.20220802.12 T2 - International Journal of Fluid Mechanics & Thermal Sciences JF - International Journal of Fluid Mechanics & Thermal Sciences JO - International Journal of Fluid Mechanics & Thermal Sciences SP - 34 EP - 40 PB - Science Publishing Group SN - 2469-8113 UR - https://doi.org/10.11648/j.ijfmts.20220802.12 AB - In pulse detonation engines (PDE), combustion temperatures can rise as high as 3000 K across the detonation wave. The continuous exposure to such elevated temperature may risk the integrity of the structural components of the engines. In order to be able to estimate the heat load accurately. Hence, numerical and experimental studies of the temperature distribution on a pulse detonation engine model was conducted to quantify the heat load. Navier-Stokes conservation equations with viscosity and chemical reaction for deflagration-to-detonation transition (DDT) in detonation engines were solved through computational fluid dynamics. Reactive flow field of premixed mixtures (propane-oxygen) was modeled for detonation process. In the simulation, short-term detonation combustion (ms) and long-term wall heating process(s) are carried out together. Both single detonation and multiple continuous detonations were simulated and tested, and the simulation results are consistent with the experimental results. The results show that there is a correlation between heat flux and detonation wave structure and the instantaneous maximum heat flux appears in the detonation wave region of the detonation tube wall. The distribution of transient heat flux in time and space is very uneven, and the difference between transient heat flux and average heat flux is large. The position of detonation wave formation is the turning point of PDE wall temperature, and the temperature at the front end of the turning point is lower than that at the back end. The results show that the fresh mixtures have cooling effect on the detonation tube wall, which leads to the increase of the inner wall temperature with oscillation and the continuous increase of the outside wall temperature. The maximum wall temperature and the speed of temperature rise are positively correlated with detonation frequency. The results also show that the heat transfer coefficient of detonation tube has an effect on the initiation of detonation wave. When the heat transfer coefficient is large, detonation wave can not initiate in the studied engine. The focus of thermal protection is different between single detonation and multiple continuous detonations. Heat management of the detonation engines highlights an important part on the engine construction. VL - 8 IS - 2 ER -
Information
Email: