Gas turbine combustion chamber

Abstract

The present invention relates to a gas-turbine combustion chamber with an outer combustion chamber wall concentric to a gas-turbine center axis and with an inner combustion chamber wall, with several burners arranged spread over the circumference of the combustion chamber, and with air inlet recesses which in at least one radial plane are provided spread over the circumference on an outer combustion chamber wall and on an inner combustion chamber wall, where the burner is designed to form a flow provided with a swirl and where air inlet recesses assigned to a burner are dimensioned in differing size in order to generate airflows of differing size, characterized in that at least one of the respective air inlet recesses is designed for supplying air in the flow direction of the swirl of the combustion chamber flow and is provided with flow guidance walls.

1 . Gas-turbine combustion chamber with an outer combustion chamber wall concentric to a gas-turbine center axis and with an inner combustion chamber wall, with several burners arranged spread over the circumference of the combustion chamber, and with air inlet recesses which in at least one radial plane are provided spread over the circumference on an outer combustion chamber wall and on an inner combustion chamber wall, where the burner is designed to form a flow provided with a swirl and where air inlet recesses assigned to a burner are dimensioned in differing size in order to generate airflows of differing size, characterized in that at least one of the respective air inlet recesses is designed for supplying air in the flow direction of the swirl, where at least one each air inlet recess is provided with flow guidance walls such that on the outer and inner combustion chamber walls one each air inlet recess is provided with a large air mass flow and the other recesses are provided with a reduced, however identical, air mass flow and that the large air inlet recesses are provided with flow guidance walls to intensify the mixture by a high jet pulse, with the swirl having the same direction as the combustion chamber flow. 
     
     
         2 . Gas-turbine combustion chamber in accordance with  claim 1 , characterized in that the mutually assigned air inlet recesses of the outer combustion chamber wall and of the inner combustion chamber wall are each arranged radially to one another or are arranged offset from one another in the circumferential direction. 
     
     
         3 . Gas-turbine combustion chamber in accordance with  claim 1 , characterized in that the mutually assigned air inlet recesses of the outer combustion chamber wall and of the inner combustion chamber wall have identical or varying spacing in the circumferential direction. 
     
     
         4 . Gas-turbine combustion chamber in accordance with  claim 1 , characterized in that all air inlet recesses are provided with flow guidance walls (chutes), where said flow guidance walls are designed with or without an inclination of the flow direction relative to the gas-turbine center axis and/or to a radial plane and/or to the circumferential direction, and are of identical or differing geometrical design. 
     
     
         5 . Gas-turbine combustion chamber in accordance with  claim 1 , characterized in that the air inlet recesses are arranged in axial stages to one another or are offset from one another. 
     
     
         6 . Gas-turbine combustion chamber in accordance with  claim 1 , characterized in that differing numbers of air inlet recesses are provided on the outer combustion chamber wall and on the inner combustion chamber wall. 
     
     
         7 . Gas-turbine combustion chamber in accordance with  claim 1 , characterized in that the individual burners are each designed for the formation of a swirl in the same or in the opposite direction to adjacent burners. 
     
     
         8 . Gas-turbine combustion chamber in accordance with  claim 1 , characterized in that the burner is designed as a lean mix burner or as a rich mix burner. 
     
     
         9 . Gas-turbine combustion chamber in accordance with  claim 1 , characterized in that one or several air inlet recesses are provided on the inner and outer combustion chamber walls per burner sector, with the number of air inlet recesses on the inner and outer combustion chamber walls being identical or differing. 
     
     
         10 . Gas-turbine combustion chamber in accordance with  claim 1 , characterized in that the swirl of the burner flow is partially or entirely generated by swirlers outside the fuel injection nozzles and that at least one of the respective air inlet recesses is designed for supplying air in the flow direction of the swirl. 
     
     
         11 . Gas-turbine combustion chamber in accordance with  claim 1 , characterized in that one or more air inlet recesses on the inner and outer combustion chamber walls are provided with non-circular air inlet recesses, for example as oblong holes, where at least the respectively largest air inlet recesses are provided with flow guidance walls.