Development of thrusts with ceramic-composite combustion chamber
- Paper number
IAC-09.C4.3.4
- Author
Prof. Alexander Alexandrovich Kozlov , Moscow Aviation Institute, Russia
- Coauthor
Mr. Alexey Gennadievich Vorobiev, Moscow Aviation Institute, Russia
- Coauthor
Mr. Igor Nikolaevich Borovik, Moscow Aviation Institute, Russia
- Year
2009
- Abstract
The department No. 202 of Moscow Aviation Institute (MAI) is researching the application of ceramic-composite combustion chamber and nozzle to existing 200 and 500 N thrusts. Using ceramic-composite materials allow reducing the mass of thrusts and increasing permissible wall temperature, which makes it possible to increasing working temperature near walls, hence specific impulse can be increased. Anti-oxidizer coatings to inner wall allow changing film-cooling component from fuel to oxidizer. In order to apply ceramic-composite materials, following technological problems must be investigated. \begin{itemize}\item forming of thin shell profile\end{itemize} \begin{itemize}\item material resistance from oxidizer environment by coating\end{itemize} \begin{itemize}\item reliable connection method between ceramic-composite combustion chamber and steel mixing head \end{itemize} \begin{itemize}\item gas impermeability of the material \end{itemize} \begin{itemize}\item maintenance of material strength under pressure and temperature conditions \end{itemize} The benefits of using such materials are demonstrated by the mathematical model of heat state of LRE calculation and preliminary fire tests of 200 N and 500 N thrusts.
- Abstract document
- Manuscript document
IAC-09.C4.3.4.pdf (🔒 authorized access only).
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