Research on Combustion Chamber Structure Improvement and Ignition System of Missile Turbojet Engine for Diesel Fuel
To meet the conditions of diesel ignition, this paper presents several structural improvements of a small missile turbojet engine for diesel fuel. The engine starts motor-assisted, and its fuel is ignited by silicon nitride ceramic ignitor. Theoretical analysis is performed by establishing a mathema...
| Main Authors: | , , , , , |
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| 格式: | 文件 |
| 语言: | English |
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Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek
2018-01-01
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| 丛编: | Tehnički Vjesnik |
| 主题: | |
| 在线阅读: | https://hrcak.srce.hr/file/311143 |
| _version_ | 1827282770920996864 |
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| author | Lei Qiu Xi Zeng Shiming Ji Fengfei Xi Wenbin Qiu Qianqian Zheng |
| author_facet | Lei Qiu Xi Zeng Shiming Ji Fengfei Xi Wenbin Qiu Qianqian Zheng |
| author_sort | Lei Qiu |
| collection | DOAJ |
| description | To meet the conditions of diesel ignition, this paper presents several structural improvements of a small missile turbojet engine for diesel fuel. The engine starts motor-assisted, and its fuel is ignited by silicon nitride ceramic ignitor. Theoretical analysis is performed by establishing a mathematical model of the combustion model and combustion conditions. The feasibility of diesel used as a small turbojet fuel is analyzed by using numerical simulation software. Research is carried out based on the following points: the improvement of combustion chamber and evaporator, selection of ignitor position and sustainability of fire. This paper proposed the method of linking the engine-assisting startup system and selected the right type of ignitor, and on the advanced experimental platform several groups ignition tests were carried out. |
| first_indexed | 2024-04-24T09:24:51Z |
| format | Article |
| id | doaj.art-9103f6fecd16411d90a6b60f41eb0b26 |
| institution | Directory Open Access Journal |
| issn | 1330-3651 1848-6339 |
| language | English |
| last_indexed | 2024-04-24T09:24:51Z |
| publishDate | 2018-01-01 |
| publisher | Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek |
| record_format | Article |
| series | Tehnički Vjesnik |
| spelling | doaj.art-9103f6fecd16411d90a6b60f41eb0b262024-04-15T15:13:01ZengFaculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in OsijekTehnički Vjesnik1330-36511848-63392018-01-012561792180010.17559/TV-20180807223114Research on Combustion Chamber Structure Improvement and Ignition System of Missile Turbojet Engine for Diesel FuelLei Qiu0Xi Zeng1Shiming Ji2Fengfei Xi3Wenbin Qiu4Qianqian Zheng5Key Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, China / Zhejiang University of Technology, Hangzhou, ChinaKey Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, China / Zhejiang University of Technology, Hangzhou, ChinaKey Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, ChinaKey Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, ChinaKey Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, ChinaKey Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, ChinaTo meet the conditions of diesel ignition, this paper presents several structural improvements of a small missile turbojet engine for diesel fuel. The engine starts motor-assisted, and its fuel is ignited by silicon nitride ceramic ignitor. Theoretical analysis is performed by establishing a mathematical model of the combustion model and combustion conditions. The feasibility of diesel used as a small turbojet fuel is analyzed by using numerical simulation software. Research is carried out based on the following points: the improvement of combustion chamber and evaporator, selection of ignitor position and sustainability of fire. This paper proposed the method of linking the engine-assisting startup system and selected the right type of ignitor, and on the advanced experimental platform several groups ignition tests were carried out.https://hrcak.srce.hr/file/311143combustion chamberdieselignition systemmissileturbojet |
| spellingShingle | Lei Qiu Xi Zeng Shiming Ji Fengfei Xi Wenbin Qiu Qianqian Zheng Research on Combustion Chamber Structure Improvement and Ignition System of Missile Turbojet Engine for Diesel Fuel Tehnički Vjesnik combustion chamber diesel ignition system missile turbojet |
| title | Research on Combustion Chamber Structure Improvement and Ignition System of Missile Turbojet Engine for Diesel Fuel |
| title_full | Research on Combustion Chamber Structure Improvement and Ignition System of Missile Turbojet Engine for Diesel Fuel |
| title_fullStr | Research on Combustion Chamber Structure Improvement and Ignition System of Missile Turbojet Engine for Diesel Fuel |
| title_full_unstemmed | Research on Combustion Chamber Structure Improvement and Ignition System of Missile Turbojet Engine for Diesel Fuel |
| title_short | Research on Combustion Chamber Structure Improvement and Ignition System of Missile Turbojet Engine for Diesel Fuel |
| title_sort | research on combustion chamber structure improvement and ignition system of missile turbojet engine for diesel fuel |
| topic | combustion chamber diesel ignition system missile turbojet |
| url | https://hrcak.srce.hr/file/311143 |
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