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This invention relates to a combustion chamber particularly adapted for use in the propulsion of rockets or rocket craft. Such chambers are frequently used for combustion of a mixture of liquids, such as gasoline and liquid oxygen, which combustion develops an extremely high temperature, sometimes in excess of 4000˚ F. It is the general object of my present invention to provide an improved construction in a combustion chamber, by which reliable and efficient operation under extreme conditions is assured. I also provide a combustion chamber which is of simple construction and of relatively light weight and which is thereby well adapted for aircraft purposes.
combustion chambers, aircraft combustion chambers, light weight combustion chambers
Aerospace Engineering | Heat Transfer, Combustion | Mechanical Engineering
Goddard, Robert, "Combustion Chamber" (1942). WPI Patents Collection. 66.