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The invention relates to a cooling channel for a component conveying hot gas for the purposes of conveying a coolant along a direction of flow with a downstream and an upstream side, with a plurality of inlet apertures for a coolant, with a number of inlet apertures that vary their configuration at

The invention relates to a cooling channel for a component conveying hot gas for the purposes of conveying a coolant along a direction of flow with a downstream and an upstream side, with a plurality of inlet apertures for a coolant, with a number of inlet apertures that vary their configuration at least partly among themselves is arranged at least in one section of the cooling channel. As a result, the heat-transfer coefficient is substantially increased at points particularly requiring cooling and therefore the cooling is substantially improved. The cooling channel is characterized by a particularly low pressure loss. Furthermore, a combustion chamber with a cooling channel of this type is specified.

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1. A cooling channel for conveying a coolant along a direction of flow, comprising: a plurality of channel walls having a downstream and an upstream side with respect to the direction of coolant flow where a first channel wall is operatively exposed to a hot combustion gas, a second channel wall is

1. A cooling channel for conveying a coolant along a direction of flow, comprising: a plurality of channel walls having a downstream and an upstream side with respect to the direction of coolant flow where a first channel wall is operatively exposed to a hot combustion gas, a second channel wall is disposed opposite the first channel wall, and side walls, each spanning from the first channel wall to the second channel wall; anda plurality of inlet apertures arranged in a plurality of rows around the perimeter of at least the second channel wall for the inlet of the coolant to the cooling channel at the upstream side, wherein the plurality of rows are arranged in the direction of flow, wherein the plurality of inlet apertures are axially aligned with the cooling channel and radially outward of the first channel wall, wherein the inlet apertures vary in size and/or shape among themselves, wherein each inlet aperture comprises an aperture entry and an aperture exit, and wherein at the upstream side the cooling channel terminates at an end wall disposed upstream of the aperture exits and joining the first channel wall, the second channel wall, and the side walls such that the inlet apertures supply all coolant for the coolant flow in the cooling channel. 2. The cooling channel as claimed in claim 1, wherein the configuration of the inlet apertures includes at least one geometry of the inlet apertures. 3. The cooling channel as claimed in claim 1, wherein the configuration of each of the inlet apertures includes a circular coolant inlet periphery and/or another geometrical shape. 4. The cooling channel as claimed in claim 1, wherein a plurality of the cooling inlet apertures comprise different coolant inlet peripheries. 5. The cooling channel as claimed in claim 4, wherein the coolant inlet periphery of the cooling inlet apertures arranged downstream is larger than the coolant inlet periphery of the cooling inlet apertures arranged upstream. 6. The cooling channel as claimed in claim 4, wherein the coolant inlet periphery of the cooling inlet apertures arranged downstream is smaller than the coolant inlet periphery of the cooling inlet apertures arranged upstream. 7. The cooling channel as claimed in claim 4, wherein the cooling inlet apertures are arranged in columns transversely with respect to the direction of flow and in a plurality of rows in the direction of flow. 8. The cooling channel as claimed in claim 7, wherein the coolant inlet periphery of the cooling inlet apertures varies from column to column in each case. 9. The cooling channel as claimed in claim 1, wherein at least one vortex-forming and/or turbulence-forming device is arranged in the cooling channel for removing heat from the channel wall arranged on the hot combustion gas side. 10. The cooling channel as claimed in claim 9, wherein the vortex-forming or as applicable turbulence-forming device is arranged in the region of points particularly requiring cooling in the cooling channel. 11. The cooling channel as claimed in claim 10, wherein the channel wall of the cooling channel facing the hot combustion gas comprises concave depressions exposed to the coolant. 12. The cooling channel as claimed in claim 11, wherein the configuration of the inlet aperture generates a counter-rotating vortex in the region of the depressions in the cooling channel. 13. The cooling channel as claimed in claim 1, wherein at least one inlet aperture is defined at least in part by an inlet vane. 14. The cooling channel as claimed in claim 13, wherein the inlet vane is arranged upstream of the cooling channel. 15. The cooling channel as claimed in claim 1, wherein at least one of the inlet apertures is angled to direct a portion of the flow into a corner region at an upstream most end of the cooling channel. 16. The cooling channel as claimed in claim 1, wherein the inlet apertures are effective to reduce a secondary flow within the flow and proximate the side walls. 17. A cooled combustion chamber, comprising: a combustion space arranged within the combustion chamber;a burner arranged within the combustion space that admits a fuel to be combusted in the combustion space to produce a hot combustion gas; anda cooling channel arranged within the combustion chamber that defines the combustion space and having: a plurality of channel walls having a downstream and an upstream side with respect to the direction of coolant flow where a first channel wall is operatively exposed to the hot combustion gas, a second channel wall is disposed opposite the first channel wall, and side walls, each spanning from the first channel wall to the second channel wall; anda plurality of inlet apertures arranged in a plurality of rows around the perimeter of at least the second channel wall for the inlet of the coolant to the cooling channel at the upstream side, wherein the plurality of rows are arranged in the direction of flow, wherein the plurality of inlet apertures are axially aligned with the cooling channel and radially outward of the first channel wall, wherein the inlet apertures vary in size and/or shape among themselves within at least one segment of the cooling channel, wherein the inlet apertures are effective to reduce a secondary flow within the flow and proximate the side walls, wherein each inlet aperture comprises an aperture entry and an aperture exit, and wherein at the upstream side the cooling channel terminates at an end wall disposed upstream of the aperture exits and joining the first channel wall, the second channel wall, and the side walls such that the inlet apertures supply all coolant for the coolant flow in the cooling channel. 18. A gas turbine engine, comprising: a rotor arranged along a rotational axis of the turbine;a compressor arranged coaxially with the rotor that inlets a working fluid and produces a compressed working fluid;a combustion chamber arranged downstream of the compressor that receives the compressed working fluid and comprises: a combustion space arranged within the combustion chamber,a burner arranged within the combustion space that admits a fuel to be combusted in the combustion space to produce a hot combustion gas, anda cooling channel arranged within the combustion chamber that defines the combustion space and having: a plurality of channel walls having a downstream and an upstream side with respect to the direction of coolant flow where a first channel wall is operatively exposed to the hot combustion gas, a second channel wall is disposed opposite the first channel wall, and side walls each spanning from the first channel wall to the second channel wall; anda plurality of inlet apertures arranged in a plurality of rows around the perimeter of at least the second channel wall for the inlet of the coolant to the cooling channel at the upstream side, wherein the plurality of rows are arranged in the direction of flow, wherein the plurality of inlet apertures are axially aligned with the cooling channel and radially outward of the first channel wall, wherein the inlet apertures vary in size and/or shape among themselves within at least one segment of the cooling channel, wherein the inlet apertures are effective to reduce a secondary flow within the flow and proximate the side walls, wherein each inlet aperture comprises an aperture entry and an aperture exit, and wherein at the upstream side the cooling channel terminates at an end wall disposed upstream of the aperture exits and joining the first channel wall, the second channel wall, and the side walls such that the inlet apertures supply all coolant for the coolant flow in the cooling channela turbine arranged downstream of the combustion chamber that receives and expands the hot combustion gas to produce mechanical energy. 19. The gas turbine engine as claimed in claim 18, wherein two opposite channel walls extend along the direction of flow and between which a cooling channel headspace extending transversely with respect to the direction of flow is present, and one of the two channel walls faces a hot side and the other of the two channel walls faces a cold side.