Cooled vane for gas turbine

A cooled vane for a gas turbine or similar device including a vane blade comprising:

• a suction side wall and a pressure side wall that are connected with each other through a leading edge and a trailing edge and forming a cavity extending in a radial direction through which a cooling medium is capable of flowing;
• a vane section formed by sections of the suction side wall and the pressure side wall and adjoining the trailing edge;
• a plurality of cooling channels which start at the cavity and extend through the vane section and end at the trailing edge, the plurality of cooling channels including a first row of cooling channels adjacent the suction side wall and a second row of cooling channels adjacent the pressure side wall;
• wherein the cooling channels are arranged so that a maximum width of each cooling channel is oriented outward and directly adjoining one of the suction side of the vane blade;
• and
• wherein a ratio of a maximum width of each cooling channel is in the range from 1.5 to 1.0:1.

A cooled vane for a gas turbine or similar device including a vane blade comprising:

• a suction side wall and a pressure side wall that are connected with each other through a leading edge and a trailing edge and forming a cavity extending in a radial direction through which a cooling medium is capable of flowing;
• a vane section formed by sections of the suction side wall and the pressure side wall and adjoining the trailing edge;
• a plurality of cooling channels which start at the cavity and extend through the vane section and end at the trailing edge, the plurality of cooling channels including a first row of cooling channels adjacent the suction side wall and a second row of cooling channels adjacent the pressure side wall;
• and
• wherein the spacing between adjacent cooling channels of at least one of the rows of cooling channels varies in the radial direction.

A cooled vane for a gas turbine or similar device including a vane blade comprising:

• a suction side wall and a pressure side wall that are connected with each other through a leading edge and a trailing edge and forming a cavity extending in a radial direction through which a cooling medium is capable of flowing;
• a vane section formed by sections of the suction side wall and the pressure side wall and adjoining the trailing edge;
• a plurality of cooling channels which start at the cavity and extend through the vane section and end at the trailing edge, the plurality of cooling channels including a first row of cooling adjacent the suction side wall and a second row of cooling channels adjacent the pressure side wall;
• and
• wherein the cooled vane is produced by a casting process, whereby the cooling channels are formed by a one-piece core that is removed after casting.

A cooled vane for a gas turbine or similar device including a vane blade comprising:

• a suction side wall and a pressure side wall that are connected with each other through a leading edge and a trailing edge and forming a cavity extending in a radial direction through which a cooling medium is capable of flowing;
• a vane section formed by sections of the suction side wall and the pressure side wall and adjoining the trailing edge;
• a plurality of cooling channels which start at the cavity and extend through the vane section and end at the trailing edge, the plurality of cooling channels including a first row of cooling channels adjacent the suction side wall and a second row of cooling channels adjacent the pressure side wall;
• and
• wherein the cooling channels are formed at least in section by grooves in the suction side wall and in the pressure side wall and by a dividing body inserted between the suction side wall and the pressure side wall, and wherein the dividing body is formed of an insulating material.

A cooled vane for a gas turbine or similar device including a vane blade comprising:

• a suction side wall and a pressure side wall that are connected with each other through a leading edge and a trailing edge and forming a cavity extending in a radial direction through which a cooling medium is capable of flowing;
• a plurality of cooling channels which start at the cavity and extend through the vane section and end at the trailing edge, the plurality of cooling channels including a first row of cooling channels adjacent the suction side wall and a second row of cooling channels adjacent the pressure side wall;
• and
• wherein the cross-sectional area of at least one of the rows of cooling channels in one of the rows of cooling channels is less than the cross-sectional area of another cooling channel in the same row.