Combustion-chamber arrangement of a gas turbine, comprising - an annular combustion chamber with an inner annular wall and with an outer annular wall , - a combustion-chamber head with a multiplicity of fuel nozzles , - a first dilution-air row (Z1) with a multiplicity of first dilution-air holes in the form of passage openings, which are arranged in the inner annular wall and/or the outer annular wall , - a second dilution-air row (Z2) with a multiplicity of second dilution-air holes in the form of passage openings, which are arranged in the inner annular wall and/or the outer annular wall , - wherein the first dilution-air holes have first inner centre points and first outer centre points and the second dilution-air holes have second inner centre points and second outer centre points , wherein the first and second inner centre points in each case lie on a side of the first and second dilution-air holes that is directed towards the combustion chamber , and the first and second outer centre points lie on a side of the first and second dilution-air holes that faces away from the combustion chamber , - wherein L is a distance between the first and second inner centre points and/or between the first and second outer centre points of the first and/or second dilution-air holes , - wherein D1 is a first flow diameter of the first dilution-air holes at an entry side and/or an exit side with respect to the combustion chamber and D2 is a second flow diameter of the second dilution-air holes at the entry side and/or the exit side with respect to the combustion chamber , - wherein the second flow diameter D2 is greater than the first flow diameter D1, and - wherein C is a measure for an average throughflow coefficient of the first and second dilution-air holes , characterized in that the equation L = D 2 / D 1 * D 2 − D 1 / C 2 is satisfied. - an annular combustion chamber with an inner annular wall and with an outer annular wall , - a combustion-chamber head with a multiplicity of fuel nozzles , - a first dilution-air row (Z1) with a multiplicity of first dilution-air holes in the form of passage openings, which are arranged in the inner annular wall and/or the outer annular wall , - a second dilution-air row (Z2) with a multiplicity of second dilution-air holes in the form of passage openings, which are arranged in the inner annular wall and/or the outer annular wall , - wherein the first dilution-air holes have first inner centre points and first outer centre points and the second dilution-air holes have second inner centre points and second outer centre points , wherein the first and second inner centre points in each case lie on a side of the first and second dilution-air holes that is directed towards the combustion chamber , and the first and second outer centre points lie on a side of the first and second dilution-air holes that faces away from the combustion chamber , - wherein L is a distance between the first and second inner centre points and/or between the first and second outer centre points of the first and/or second dilution-air holes , - wherein D1 is a first flow diameter of the first dilution-air holes at an entry side and/or an exit side with respect to the combustion chamber and D2 is a second flow diameter of the second dilution-air holes at the entry side and/or the exit side with respect to the combustion chamber , - wherein the second flow diameter D2 is greater than the first flow diameter D1, and - wherein C is a measure for an average throughflow coefficient of the first and second dilution-air holes , characterized in that the equation L = D 2 / D 1 * D 2 − D 1 / C 2 is satisfied. <EOS>