Combustion chamber structure for a turbojet engine

Claim 1

In a turbojet engine having a combustion chamber, the improvement comprising: (a) first and second double wall structures defining transverse limits of the combustion chamber, each double wall structure comprising: (i) a hot wall structure exposed to high temperature gases within the combustion chamber; and, (ii) a cold wall structure; and, (b) means to attach the hot wall structure to the cold wall structure so as to permit transverse movement of the hot wall with respect to the cold wall between minimum and maximum spacing while preventing relative longitudinal movement therebetween, the means comprising: (i) an orifice member defining an air orifice therethrough, extending through the cold wall and the hot wall so as to allow air to flow into the combustion chamber, the orifice member having a first generally cylindrical portion, a second generally cylindrical portion, and a first flange extending radially outwardly from the first generally cylindrical portion; and, (ii) an annular member attached to the second generally cylindrical portion of the orifice member and to the hot wall, the annular member having a second flange extending radially therefrom disposed between the hot wall and the cold wall, and spaced from the first flange such that a length of the first generally cylindrical portion extending between the first and second flanges defines the maximum amount of transverse movement between the hot and cold walls and a thickness of the second flange defines the minimum spacing between the hot and cold walls.