Gas turbine part comprising a near wall cooling arrangement

1. A combustor part of a gas turbine, comprising:

a wall, which is subjected to high temperature gas on a hot side, the wall containing a plurality of near wall cooling channels extending essentially parallel to each other in a first direction within the wall in close vicinity to the hot side and being arranged in at least one row extending in a second direction essentially perpendicular to the first direction, the at least one row having a first end and a second end, and wherein the plurality of near wall cooling channels are each provided at one end with an inlet for a supply of cooling air, and on another end with an outlet for a discharge of cooling air, wherein the inlets of the plurality of near wall cooling channels open into a common feeding channel for cooling air supply, and the outlets of the plurality of the near wall cooling channels open into a common discharge channel for cooling air discharge, the common feeding channel and the common discharge channel extending in the second direction, the common feeding channel being open at the first end and closed at the second end, the first end configured to receive supplied cooling air and guide the supplied cooling air into the inlets of the plurality of near wall cooling channels, and the common discharge channel being closed at the first end and open at the second end, the second end configured to discharge cooling air from the outlets of the plurality of near wall cooling channels, and wherein the common feeding channel and the common discharge channel each have a cross section which is constant in the second direction, and wherein the plurality of near wall cooling channels include a first channel located at the first end and a plurality of second channels located between the first channel and the second end, and wherein each of the plurality of second channels between the first channel and the second end has a smaller cross section than a respective closest upstream neighboring near wall cooling channel, with respect to a flow of the supplied cooling air.

2. The gas turbine part according to claim 1 , wherein each of the plurality of near wall cooling channels are arranged within the at least one row with an essentially constant inter-channel distance.

3. The gas turbine part according to claim 1 , comprising:

a plurality of rows of the plurality of near wall cooling channels, wherein the plurality of rows run parallel to each other in the second direction, each of the plurality of rows has a separate feeding channel and discharge channel with a common separation wall and respective outer channel walls, and wherein neighboring rows share an outer channel wall.

4. The gas turbine part according to claim 1 , wherein each of the plurality of near wall cooling channels has a circular inlet and a circular outlet.

5. The gas turbine part according to claim 1 , wherein the plurality of near wall cooling channels comprises at least three near wall cooling channels.

6. The gas turbine part according to claim 1 , wherein the gas turbine part is a combustion liner.

7. A combustor liner of a gas turbine, comprising:

a wall, which is subjected to high temperature gas on a hot side, the wall containing a plurality of near wall cooling channels extending essentially parallel to each other in a first direction within the wall in close vicinity to the hot side and being arranged in at least one row extending in a second direction essentially perpendicular to the first direction, the at least one row having a first end and a second end, and wherein the plurality of near wall cooling channels are each provided at one end with an inlet for a supply of cooling air, and on another end with an outlet for a discharge of cooling air, wherein the inlets of the plurality of near wall cooling channels open into a common feeding channel for cooling air supply, and the outlets of the plurality of the near wall cooling channels open into a common discharge channel for cooling air discharge, the common feeding channel and the common discharge channel extending in the second direction, the common feeding channel being open at the first end and closed at the second end, the first end configured to receive supplied cooling air and guide the supplied cooling air into the inlets of the plurality of near wall cooling channels, and the common discharge channel being closed at the first end and open at the second end, the second end configured to discharge cooling air from the outlets of the plurality of near wall cooling channels, and wherein the common feeding channel and the common discharge channel each have a cross section which is constant in the second direction, and wherein the plurality of near wall cooling channels include a first channel located at the first end and a plurality of second channels located between the first channel and the second end, and wherein each of the plurality of second channels between the first channel and the second end has a smaller cross section than a respective closest upstream neighboring near wall cooling channel, with respect to a flow of the supplied cooling air; and

the at least one row comprising a plurality of rows, wherein the plurality of rows run parallel to each other in the second direction, each of the plurality of rows has a separate feeding channel and discharge channel with a common separation wall and respective outer channel walls, and wherein neighboring rows share an outer channel wall.

8. The combustion liner according to claim 7 , wherein each of the plurality of near wall cooling channels are arranged within the at least one row with an essentially constant inter-channel distance.

9. The combustion liner according to claim 7 , wherein each of the plurality of near wall cooling channels has a circular inlet and a circular outlet.

10. The combustion liner according to claim 7 , wherein the plurality of near wall cooling channels comprises at least three near wall cooling channels.