An improved thermal jet for the propellant launching system
This work is focused to study the energy release and flow behavior of liquid propellant during internal ballistics cycle of liquid launching system on the base of the thermal gas jet. Especially, an improved thermal jet is proposed via new type of stepped-wall chamber structure and thus the energy r...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
Elsevier
2023-05-01
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| Series: | Case Studies in Thermal Engineering |
| Subjects: | |
| Online Access: | http://www.sciencedirect.com/science/article/pii/S2214157X23001831 |
| _version_ | 1797832755071942656 |
|---|---|
| author | Xiaochun Xue Yonggang Yu |
| author_facet | Xiaochun Xue Yonggang Yu |
| author_sort | Xiaochun Xue |
| collection | DOAJ |
| description | This work is focused to study the energy release and flow behavior of liquid propellant during internal ballistics cycle of liquid launching system on the base of the thermal gas jet. Especially, an improved thermal jet is proposed via new type of stepped-wall chamber structure and thus the energy release efficiency is also enhanced with a decrease of pressure oscillation. The combustion of the liquid propellant in this system with a base ignition strongly depends on hydrodynamic instability of gas-liquid mixing process with high temperature and high pressure. The chamber structure has been verified to be as a means for controlling the instability problem in this propulsion process and three types of stepped-wall chambers are investigated to account for the effect of the stage on the flow and energy release behavior of liquid propellant based on this improved thermal jet. For the stepped-wall structure with three stages, the local liquid can be entrained into the Taylor cavity with more intense turbulent mixture at the corner of steps because of the existence of vortices under Taylor-Helmholtz effect. The corresponding propulsion efficiency γ only reaches to 1.003 mm−2 ms−1 and the muzzle velocity of the vehicle is 911 m/s with the maximum pressure of 317 MPa. Consequently, the heat transfer process from the high-temperature combustion-gas to the liquid propellant is also enhanced for the chamber with three stages, and more liquid propellant can be involved into the chemical reaction with providing more energy for the propulsion process of the launching system. |
| first_indexed | 2024-04-09T14:12:55Z |
| format | Article |
| id | doaj.art-432330cb201b42b592e4492742f7965d |
| institution | Directory Open Access Journal |
| issn | 2214-157X |
| language | English |
| last_indexed | 2024-04-09T14:12:55Z |
| publishDate | 2023-05-01 |
| publisher | Elsevier |
| record_format | Article |
| series | Case Studies in Thermal Engineering |
| spelling | doaj.art-432330cb201b42b592e4492742f7965d2023-05-06T04:37:43ZengElsevierCase Studies in Thermal Engineering2214-157X2023-05-0145102877An improved thermal jet for the propellant launching systemXiaochun Xue0Yonggang Yu1School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing, 210094, China; National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing, 210094, ChinaSchool of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing, 210094, China; Corresponding author.This work is focused to study the energy release and flow behavior of liquid propellant during internal ballistics cycle of liquid launching system on the base of the thermal gas jet. Especially, an improved thermal jet is proposed via new type of stepped-wall chamber structure and thus the energy release efficiency is also enhanced with a decrease of pressure oscillation. The combustion of the liquid propellant in this system with a base ignition strongly depends on hydrodynamic instability of gas-liquid mixing process with high temperature and high pressure. The chamber structure has been verified to be as a means for controlling the instability problem in this propulsion process and three types of stepped-wall chambers are investigated to account for the effect of the stage on the flow and energy release behavior of liquid propellant based on this improved thermal jet. For the stepped-wall structure with three stages, the local liquid can be entrained into the Taylor cavity with more intense turbulent mixture at the corner of steps because of the existence of vortices under Taylor-Helmholtz effect. The corresponding propulsion efficiency γ only reaches to 1.003 mm−2 ms−1 and the muzzle velocity of the vehicle is 911 m/s with the maximum pressure of 317 MPa. Consequently, the heat transfer process from the high-temperature combustion-gas to the liquid propellant is also enhanced for the chamber with three stages, and more liquid propellant can be involved into the chemical reaction with providing more energy for the propulsion process of the launching system.http://www.sciencedirect.com/science/article/pii/S2214157X23001831Energy releaseThermal jetTaylor cavityKelvin-Helmholtz mixingHeat transfer |
| spellingShingle | Xiaochun Xue Yonggang Yu An improved thermal jet for the propellant launching system Case Studies in Thermal Engineering Energy release Thermal jet Taylor cavity Kelvin-Helmholtz mixing Heat transfer |
| title | An improved thermal jet for the propellant launching system |
| title_full | An improved thermal jet for the propellant launching system |
| title_fullStr | An improved thermal jet for the propellant launching system |
| title_full_unstemmed | An improved thermal jet for the propellant launching system |
| title_short | An improved thermal jet for the propellant launching system |
| title_sort | improved thermal jet for the propellant launching system |
| topic | Energy release Thermal jet Taylor cavity Kelvin-Helmholtz mixing Heat transfer |
| url | http://www.sciencedirect.com/science/article/pii/S2214157X23001831 |
| work_keys_str_mv | AT xiaochunxue animprovedthermaljetforthepropellantlaunchingsystem AT yonggangyu animprovedthermaljetforthepropellantlaunchingsystem AT xiaochunxue improvedthermaljetforthepropellantlaunchingsystem AT yonggangyu improvedthermaljetforthepropellantlaunchingsystem |