초록 ▼

The invention concerns a combustion chamber whereof the inner wall (17)is made at least partly of a thermostructural composite material, which is porous to the fuel passing through the double wall (14); and the porosity of said inner wall (17) is adjusted so that the proportion of said fuel passing

The invention concerns a combustion chamber whereof the inner wall (17)is made at least partly of a thermostructural composite material, which is porous to the fuel passing through the double wall (14); and the porosity of said inner wall (17) is adjusted so that the proportion of said fuel passing through said inner skin ranges between 5% and 15% of the total amount of fuel input in said ramjet engine.

대표청구항 ▼

The invention claimed is: 1. A ramjet having an elongate body, the ramjet comprising: at one end of said body, an inlet for a stream of oxidizer; at an intermediate part of said body, a combustion chamber which is provided with at least one fuel injector and in the heart of which the oxidizer and

The invention claimed is: 1. A ramjet having an elongate body, the ramjet comprising: at one end of said body, an inlet for a stream of oxidizer; at an intermediate part of said body, a combustion chamber which is provided with at least one fuel injector and in the heart of which the oxidizer and fuel mix and said mixture is burnt, the wall of said combustion chamber consisting at least in part of an inner skin arranged on the same side as said heart and an outer skin spaced away from said inner skin forming therewith an intermediate space and said fuel supplying said injector passing, at least in part, through said intermediate space to cool said wall; and at the other end of said body, an exhaust jetpipe ducting the combustion gases leaving the heart of said combustion chamber, wherein: said inner skin is made at least in part of a thermostructural composite, which is porous to said fuel passing through said intermediate space; the porosity of said inner skin is set so that the proportion of said fuel passing through said inner skin is between 5% and 15% of the total amount of fuel supplied for said ramjet; said outer skin is made of a thermostructural composite that is sealed against liquids and gases; and said inner and outer skins made of thermostructural composite are adjoined together by a plurality of threadlike spacers of thermostructural composite passing across said intermediate space. 2. The ramjet as claimed in claim 1, wherein said combustion chamber consists of a single piece in which the walls are all joined together and form a closed prismatic surface. 3. The ramjet as claimed in claim 1, wherein said combustion chamber has four walls in opposed pairs, giving it a closed rectangular cross section. 4. The ramjet as claimed in claim 1, wherein said combustion chamber is made of two pieces, with at least one of the walls of said combustion chamber able to move with respect to the collection of the others which are joined together. 5. The ramjet as claimed in claim 4, wherein said combustion chamber has four walls in opposed pairs, three of said walls being joined together to form a trough with a U-shaped cross section, while the fourth wall is mounted so that it can move inside said trough. 6. The ramjet as claimed in claim 1, wherein said ends of said ramjet body, respectively forming the inlet for the stream of oxidizer and the jetpipe for exhausting the combustion gases, are made of thermostructural composite and are joined to said combustion chamber. 7. The ramjet as claimed in claim 6, wherein said ends of said ramjet body form just one piece of thermostructural composite, in which said combustion chamber is incorporated.