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

IAC-09.C4.3.4.pdf

Manuscript document

IAC-09.C4.3.4.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.