Rotating Combustion Chamber for Rocket Apparatus

This invention relates to rocket apparatus adapted for use in aircraft, and relates more particularly to rocket apparatus in which the combustion chamber is rotated during the combustion operation. It is one important object of my invention to provide means for directly increasing the feed pressure of the coacting combustion liquids by the rotation of the combustion chamber itself and by a very simple and reliable construction thereof. I also provide means for producing initial rotation of the combustion chamber; means for controlling the speed of rotation of the chamber; automatic means to counteract the gyroscopic effect of the rotating chamber; means to prevent the escape of combustion liquids from the apparatus; improved means for jacketing and cooling the walls of the combustion chamber and its associated discharge nozzle; and improved means for jacketing and cooling the walls of the combustion chamber and its associated discharge nozzle; and improved means for effecting high-speed injection of a combustion mixture into the body of the combustion chamber. Another feature of the invention is the attainment of very thorough mixing and high-speed injection of the combustion liquids by preliminary combustion of a small or fractional amount of said liquids.https://digitalcommons.wpi.edu/patents/1073/thumbnail.jp