Technical gazette, Vol. 25 No. 6, 2018.
Original scientific paper
https://doi.org/10.17559/TV-20180807223114
Research on Combustion Chamber Structure Improvement and Ignition System of Missile Turbojet Engine for Diesel Fuel
Lei Qiu
; Key Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, China / Zhejiang University of Technology, Hangzhou, China
Xi Zeng
; Key Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, China / Zhejiang University of Technology, Hangzhou, China
Shiming Ji
; Key Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, China
Fengfei Xi
; Key Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, China
Wenbin Qiu
; Key Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, China
Qianqian Zheng
; Key Laboratory of E&M, Ministry of Education & Zhejiang Province, Hangzhou, China
Abstract
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.
Keywords
combustion chamber; diesel; ignition system; missile; turbojet
Hrčak ID:
212836
URI
Publication date:
16.12.2018.
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