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Arrangement of cooling channels for rocket engine combustion chambers

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专利汇可以提供Arrangement of cooling channels for rocket engine combustion chambers专利检索,专利查询,专利分析的服务。并且Longitudinally extending coolant channels are formed by means of a cutting tool in a monolithic tubular wall section used as the convergent-divergent thrust nozzle for a rocket engine combustion chamber. The width of the channels at particular locations along their length is established in inverse relationship to the amount of heat to be removed from the combustion chamber at that location. In forming the coolant channels their side wall planes are established and radial planes of the tubular wall section are formed in parallel relationship with the side wall planes. The cutting tool is aligned in the radial planes and then is displaced laterally into the side wall planes for cutting the channels. The number of passes required for the cutting operation depends on the width of the tool and the width of the channel which varies over the length of the combustion chamber.,下面是Arrangement of cooling channels for rocket engine combustion chambers专利的具体信息内容。

1. A wall member for a rocket engine combustion chamber comprising a longitudinally extending monolithic tubular wall section having a cylindrically-shaped section at one end, a diverging section at the other end, and a converging section extending between said cylindrically shaped section and said diverging section and tapering inwardly toward the axis of said tubular wall section from said cylindrically shaped section to the smaller diameter end of said diverging section, a multiplicity of separate coolant channels extending longitudinally along the outer surface of said wall section and being continuous for the axial length of said tubular wall member, said channels having a variable cross sectional area along their length in accordance with the temperature conditions experienced within the rocket engine combustion chamber, the width of said flow channels being substantially uniform for the extent of said cylindrically-shaped section then diminishing to a minimum in the transition plane from said converging section to said diverging section and increasing from the transition plane to the end of said diverging section and width of the channels varying in direct relationship to the diameter of the tubular wall section in its different sections, the longitudinally extending side walls of said channels being disposed in planes parallel with and offset from radial planes extending through the longitudinal axis of the tubular wall section with the planes of said side walls of each said coolant channel in each of the different sections of said tubular wall section intersecting at a location offset from the longitudInal axis of said tubular wall section, and each said coolant channel having a plane of symmetry dividing said channel and extending through the axis of said tubular wall section and the plane of symmetry of each said coolant channel and the planes of the opposite said side walls of each said coolant channel intersecting at a location offset from the longitudinal axis of said tubular wall section.
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