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This invention relates to a combustion chamber particularly designed for use in rockets, rocket planes and other aircraft in which continuous combustion of liquid constituents takes place at a vey high temperature. Effective provision for cooling the walls of such combustion chambers without substantial addition of weight is thus very important. It is the general object of my invention to provide an improved construction in light-weight combustion chambers, such that the chamber wall is effectively cooled; that one of the liquid constituents is simultaneously vaporized, with absorption of latent heat; and the two combustion constituents are intimately mixed adjacent the chamber wall. A further object is to provide a combustion chamber of relatively light weight which is well adapted to resist external pressure.
combustion, combustion chambers, light weight combustion chambers,
Aerospace Engineering | Heat Transfer, Combustion
Goddard, Robert, "Combustion Chamber for Aircraft" (1939). WPI Patents Collection. 65.