Arrangement of cooling chambers for rocket engine combustion chambers专利检索-发散冷却空气动力学专利检索查询-专利查询网

Arrangement of cooling chambers for rocket engine combustion chambers

阅读：663发布：2021-10-03

专利汇可以提供Arrangement of cooling chambers 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 chambers for rocket engine combustion chambers专利的具体信息内容。

权利要求

1. A method of forming coolant channels in a rocket engine combustion chamber formed by an elongated monolithic tubular wall section symmetrically arranged about a longitudinally extending central axis and having a cylindrically shaped section at one end, a diverging section at the other end and a converging section tapering inwardly from and extending between the cylindrically shaped section to the small diameter end of the diverging section, in consideration of the determined dimensions of the coolant channels and the location of the cutting planes defining the lateral sides of the coolant channels in the cylindrically shaped, converging and diverging sections of the tubular wall section as based on the thermal conditions existing in the combustion chamber and with the channel widths in the different sections being based on a diameter proportionality of the sections, the steps of forming the channels comprising locating a cutting member outwardly from the tubular wall section and in a plane of symmetry bisecting the angle formed between the opposite cutting planes defining the longitudinally extending sides of the channel to be formed and extending through the longitudinally extending central axis of the tubular wall section, rotating the tubular wall section about its longitudinally extending central axis for displacing the cutting member into a radial plane of the tubular wall section adjacent to the cutting plane of the channel, displacing the cutting member laterally from the radial plane into the cutting plane and locating the side of the cutting member more remote from the plane of symmetry in the cutting plane while maintaining the cutting member in parallel relationship with its position in the adjacent radial plane, and operating the cutting member along the exterior surface of the tubular wall section while maintaining the cutting member in the cutting plane parallel to the radial plane between one end of the tubular wall section and the transition point between the converging and diverging sections, repeating the positioning of thE cutting member into the opposite side wall cutting plane of the coolant channel and operating the cutting member for forming the other side wall of the cooling channel to the required depth, repositioning the cutting member intermediate the side wall cutting planes for removing any portion of the tubular wall section within the channel remaining between the cutting planes, and repeating the positioning and cutting steps for forming the coolant channels between the opposite end of the tubular wall section and the transition plane between the converging and diverging sections.

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Arrangement of cooling chambers for rocket engine combustion chambers

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