초록 ▼

An axially stepped annular combustion chamber, especially of an aircraft gas turbine, has an essentially independent main combustion chamber 5' as well as an independent pilot burner chamber 5. An appropriate design of internal limiting walls 6a, 6b of pilot burner chamber 5 ensures that the combust

An axially stepped annular combustion chamber, especially of an aircraft gas turbine, has an essentially independent main combustion chamber 5' as well as an independent pilot burner chamber 5. An appropriate design of internal limiting walls 6a, 6b of pilot burner chamber 5 ensures that the combustion gases enter the main burner zone 5' essentially in the radial direction. This ensures optimum mixing of the fuel with air in this main combustion zone and/or main combustion chamber 5', thus minimizing exhaust emissions and ensuring optimum temperature distribution at combustion chamber outlet 8. Internal limiting wall 6a can have a deflecting section 12 or outer wall section 6b can run at an angle to pilot burner lengthwise axis 3a, so that the cross section of pilot burner zone 5 is reduced in the flow direction.

대표청구항 ▼

[ What is claimed:] [1.] 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 lo

[ What is claimed:] [1.] 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.