Review on pressure swirl injector in liquid rocket engine
The pressure swirl injector with tangential inlet ports is widely used in liquid rocket engine. Commonly, this type of pressure swirl injector consists of tangential inlet ports, a swirl chamber, a converging spin chamber, and a discharge orifice. The atomization of the liquid propellants includes t...
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| Veröffentlicht in: | Acta astronautica 2018-04, Vol.145, p.174-198 |
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| creator | Kang, Zhongtao Wang, Zhen-guo Li, Qinglian Cheng, Peng |
| description | The pressure swirl injector with tangential inlet ports is widely used in liquid rocket engine. Commonly, this type of pressure swirl injector consists of tangential inlet ports, a swirl chamber, a converging spin chamber, and a discharge orifice. The atomization of the liquid propellants includes the formation of liquid film, primary breakup and secondary atomization. And the back pressure and temperature in the combustion chamber could have great influence on the atomization of the injector. What's more, when the combustion instability occurs, the pressure oscillation could further affects the atomization process. This paper reviewed the primary atomization and the performance of the pressure swirl injector, which include the formation of the conical liquid film, the breakup and atomization characteristics of the conical liquid film, the effects of the rocket engine environment, and the response of the injector and atomization on the pressure oscillation. |
| doi_str_mv | 10.1016/j.actaastro.2017.12.038 |
| format | Article |
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Commonly, this type of pressure swirl injector consists of tangential inlet ports, a swirl chamber, a converging spin chamber, and a discharge orifice. The atomization of the liquid propellants includes the formation of liquid film, primary breakup and secondary atomization. And the back pressure and temperature in the combustion chamber could have great influence on the atomization of the injector. What's more, when the combustion instability occurs, the pressure oscillation could further affects the atomization process. This paper reviewed the primary atomization and the performance of the pressure swirl injector, which include the formation of the conical liquid film, the breakup and atomization characteristics of the conical liquid film, the effects of the rocket engine environment, and the response of the injector and atomization on the pressure oscillation.</description><identifier>ISSN: 0094-5765</identifier><identifier>EISSN: 1879-2030</identifier><identifier>DOI: 10.1016/j.actaastro.2017.12.038</identifier><language>eng</language><publisher>Elmsford: Elsevier Ltd</publisher><subject>Atomizing ; Breakup ; Combustion ; Combustion chambers ; Combustion stability ; Environmental effects ; Evaporation ; Gas turbines ; Injectors ; Instability ; Kinetics ; Liquid propellants ; Liquid rocket engine ; Orifices ; Ports ; Pressure oscillations ; Pressure swirl injector ; Review ; Rocket engines ; Rockets ; Spacecraft</subject><ispartof>Acta astronautica, 2018-04, Vol.145, p.174-198</ispartof><rights>2018 IAA</rights><rights>Copyright Elsevier BV Apr 2018</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c343t-eae3c2e781a6756261488f8d0209ff3ab83d061d7505c5bdb7e51795c6ecd6063</citedby><cites>FETCH-LOGICAL-c343t-eae3c2e781a6756261488f8d0209ff3ab83d061d7505c5bdb7e51795c6ecd6063</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://dx.doi.org/10.1016/j.actaastro.2017.12.038$$EHTML$$P50$$Gelsevier$$H</linktohtml><link.rule.ids>314,780,784,3549,27923,27924,45994</link.rule.ids></links><search><creatorcontrib>Kang, Zhongtao</creatorcontrib><creatorcontrib>Wang, Zhen-guo</creatorcontrib><creatorcontrib>Li, Qinglian</creatorcontrib><creatorcontrib>Cheng, Peng</creatorcontrib><title>Review on pressure swirl injector in liquid rocket engine</title><title>Acta astronautica</title><description>The pressure swirl injector with tangential inlet ports is widely used in liquid rocket engine. 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Commonly, this type of pressure swirl injector consists of tangential inlet ports, a swirl chamber, a converging spin chamber, and a discharge orifice. The atomization of the liquid propellants includes the formation of liquid film, primary breakup and secondary atomization. And the back pressure and temperature in the combustion chamber could have great influence on the atomization of the injector. What's more, when the combustion instability occurs, the pressure oscillation could further affects the atomization process. This paper reviewed the primary atomization and the performance of the pressure swirl injector, which include the formation of the conical liquid film, the breakup and atomization characteristics of the conical liquid film, the effects of the rocket engine environment, and the response of the injector and atomization on the pressure oscillation.</abstract><cop>Elmsford</cop><pub>Elsevier Ltd</pub><doi>10.1016/j.actaastro.2017.12.038</doi><tpages>25</tpages></addata></record> |
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| identifier | ISSN: 0094-5765 |
| ispartof | Acta astronautica, 2018-04, Vol.145, p.174-198 |
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| language | eng |
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| source | ScienceDirect Journals (5 years ago - present) |
| subjects | Atomizing Breakup Combustion Combustion chambers Combustion stability Environmental effects Evaporation Gas turbines Injectors Instability Kinetics Liquid propellants Liquid rocket engine Orifices Ports Pressure oscillations Pressure swirl injector Review Rocket engines Rockets Spacecraft |
| title | Review on pressure swirl injector in liquid rocket engine |
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