Patent ID: 10712006

Abstract:
A gas turbine combustion chamber includes first admixing air holes having first inner and outer center points, and second admixing air holes having second inner and outer center points. The first and second inner center points respectively lie on a side of the first and second admixing air holes oriented towards the combustion chamber. The first and second outer center points lie on a side of the first and second admixing air holes facing away from the combustion chamber. An equation L=D2/D1*(D2−D1)/C2 is fulfilled, with L being a distance between the first and second inner center points and/or the first and second outer center points; D1 and D2 being flow diameters of the first and second admixing air holes respectively at an entry and/or exit side to the combustion chamber and C being an average flow rate coefficient of the first and second admixing holes.