초록 ▼

A combustion chamber for a gas turbine engine has a wall which is provided with rows of apertures. The apertures are arranged so that the axes of the apertures form an angle of between 25°and 35°with respect to the inner surface of the wall. The apertures have a first cylindrical portion and a secon

A combustion chamber for a gas turbine engine has a wall which is provided with rows of apertures. The apertures are arranged so that the axes of the apertures form an angle of between 25°and 35°with respect to the inner surface of the wall. The apertures have a first cylindrical portion and a second divergent portion to produce fan shaped apertures. An upstream portion of the wall has apertures arranged in axially spaced groups, each of which has three rows of apertures and a downstream portion of the wall has apertures arranged in axially spaced groups, each of which has two rows of apertures. The axes of adjacent apertures in each row are spaced apart by at least three times the diameter of the cylindrical portion. The apertures produce effective film cooling of the wall using less cooling air than conventional cooling rings. The apertures may be arranged locally to cope with hot spots.

대표청구항 ▼

A combustion chamber for a gas turbine engine comprising at least one annular wall defining at least partially the combustion chamber, said combustion chamber having a longitudinal axis, an upstream end and a downstream end, said annular wall having a first, outwardly facing surface, a second inward

A combustion chamber for a gas turbine engine comprising at least one annular wall defining at least partially the combustion chamber, said combustion chamber having a longitudinal axis, an upstream end and a downstream end, said annular wall having a first, outwardly facing surface, a second inwardly facing surface and a plurality of rows of cooling air apertures extending through said wall with said apertures in each row being spaced apart circumferentially on said wall, each said aperture in each said row having one end on said first surface and an opposite end on said second surface and having a central, longitudinal axis extending from said first to said second surface, each said central longitudinal axis of each aperture intersecting said second surface at an angle of between 20°and 40°, each aperture being oriented to extend generally from said upstream end toward said downstream end of said combustion chamber, each said aperture having a first portion and a second portion, said first portion extending from said one end to a position intermediate said first and second surfaces of said wall, said second portion of each aperture extending from said intermediate position to said opposite end on said second surface of said wall, each said second portion increasing in cross-sectional area as the distance from said intermediate position increases with the dimensional increase being largest in the direction of the circumference of said annular wall.