| 主权项 |
1. A gas turbine combustion chamber comprising:
an outer housing portion (1); a flame tube (2) disposed within said outer housing portion; a perforated plate (3) at least partially surrounding said flame tube (2) and having an upper end face and a lower end face, each end face being fastened, at a respective fastening point, to a respective end of said outer housing portion, said perforated plate having cooling apertures (4) at least in a primary combustion area of said flame tube for impingement cooling of the flame tube (2); and a radial swirler (5) having an end plate (6), one of said end faces of said perforated plate being fastened to said end plate (6), wherein said outer housing portion and said perforated plate (3) define an annular chamber therebetween configured to impinge combustion air (L) on said perforated plate (3), the annular chamber (1) being further defined by a distance between the respective fastening points, and wherein the outer housing portion, the perforated plate (3), the respective fastening points, the end plate (6) and the radial swirler (5) are configured to cooperate with one another such that all of the combustion air is used initially to cool the flame tube (2) and then flows through the radial swirler. |
