Transitional region for a combustion chamber of a gas turbine

摘要

A gas turbine including a combustion chamber and a first row of guide vanes, arranged essentially directly downstream thereof, of a turbine. The outer and/or inner limitation of the combustion chamber defined by at least one outer and/or inner heat shield, mounted on at least one combustion chamber structure arranged radially outside and/or inside. The hot gases flow path in the region of the guide vane row being restricted radially on the outside and/or inside by an outer and/or inner vane platform, mounted at least indirectly on at least one turbine carrier. A minimal gap size directly upstream of the first row of guide vanes is achieved by mounting at least indirectly on the turbine carrier at least one mini heat shield, arranged upstream of the first row of guide vanes and essentially adjacent the vane platform and in the flow direction between the heat shield and the vane platform.

主权项

1. A gas turbine (22) comprising:
at least one combustion chamber (9) and a first row of guide vanes (2) arranged directly downstream of the combustion chamber, wherein at least one of radially outer and radially inner limitations of the combustion chamber (9) being defined by a respective outer or inner heat shield (7), which is mounted on at least one combustion chamber structure (6) arranged at least one of radially outside and radially inside, respectively, of the at least one combustion chamber structure; a flow path of hot gases (10) in a region of the first row of guide vanes (2) being restricted radially on the outside and/or radially on the inside by an outer and/or inner vane platform (3), which is mounted at least indirectly on at least one turbine carrier (4); at least one mini heat shield (13) is mounted at least indirectly on the at least one turbine carrier (4), arranged upstream of the first row of guide vanes (2) and essentially adjacent the outer and/or inner vane platform (3), and in the flow path direction (10) between the respective outer and/or inner heat shield (7) and the outer and/or inner vane platform (3), and forming a flow wall therebetween in the form of a shape adapted to the flow, with an upstream gap (17) disposed between the at least one mini heat shield (13) and the respective outer and/or inner heat shield (7), wherein the upstream gap (17) extends directly between and separates the turbine carrier (4, 18) and the combustion chamber structure (6).