Patent ID: 6058710
Filing Date: 2000-05-09
Classification: F23R

Abstract:
An axially staged annular combustion chamber of a gas turbine having a central axis, comprising:a plurality of pilot burners arranged between inner and outer annular wall sections;main burners having ends terminating downstream of said plurality of pilot burners and being located radially outward from said pilot burners in said combustion chamber, said main burners abutting a main burner zone having outer and inner combustion chamber walls which are both annular in shape and extend up to a combustion chamber outlet, said inner combustion chamber wall in an area of a pilot burner zone forming the inner annular wall section running essentially parallel to a pilot burner axis;wherein said inner combustion chamber wall abuts the inner annular wall section, which forms the pilot burner zone and runs essentially in parallel to the central axis, said inner combustion chamber wall having a deflecting section which is convex-concave in shape and runs toward the main burner zone relative to the combustion chamber when viewed in a downstream direction; andwherein said deflection section, when viewed in a radial direction relative to a central axis, ends approximately at a radial level of the outer annular wall section and abuts a downstream wall section of the inner combustion chamber wall defining the main burner zone leading to the combustion chamber outlet.