Gas turbine blade with inner and outer cooling holes
The gas turbine blade includes a cooling channel formed therein, and a partition disposed on its tip side for isolating the cooling channel from the outside. The partition is integrally formed with a blade portion in a position on its inner side in the radial direction with respect to the tip of the gas turbine blade. Reinforcements are provided on the outer side of the partition in the radial direction and on the inner side of the tip end wall extended from the blade portion to connect the partition with the tip end wall. Outer surface cooling holes are formed to extend from the cooling channel into communication with an outer surface of the tip end wall, and inner surface cooling holes are formed to extend from the cooling channel into an inner surface of the tip end wall through the partition.
1. A gas turbine blade, comprising:
a cooling channel formed in the gas turbine blade;
a partition disposed on a tip side of the blade for isolating the cooling channel from an outside of the blade;
a tip end wall formed to extend from a tip of a blade portion toward the outside in a radial direction;
a plurality of reinforcements provided along a boundary between an outer surface of the partition and an inner surface of the tip end wall, the reinforcements being spaced apart from each other;
a plurality of outer surface cooling holes extending from the cooling channel into communication with an outer surface of the blade portion; and
a plurality of inner surface cooling holes extending from the cooling channel into communication with the inner surface of the tip end wall through the partition, wherein
at least one of the plurality of inner surface cooling holes is disposed between adjacent reinforcements,
one of said outer surface cooling holes is disposed to have a part superimposed over an arrangement area of one of said reinforcements when viewing the blade portion from the outside in the radial direction,
the reinforcements are integrally casted or bonded to the partition outer surface and the tip end wall inner surface, and
the one of said outer surface cooling holes passes through the partition and the tip end wall from the cooling channel and communicates with the outer surface of the blade portion.
2. The gas turbine blade according to claim 1 , wherein the at least one of the plurality of inner surface cooling holes is in communication with the cooling channel and a space outside the blade.
3. The gas turbine blade according to claim 2 , wherein a cooling medium is injected from the at least one of the inner surface cooling holes along the inner surface of the tip end wall or toward the inner surface of the tip end wall.
4. The gas turbine blade according to claim 1 , wherein the outer surface cooling hole has an opening formed at an outer surface of the tip end wall.
5. The gas turbine blade according to claim 4 , wherein the central axis of the plurality of outer surface cooling holes is positioned in an outer diameter direction with respect to a line of intersection of a surface forming an inner surface of the tip end wall and a surface forming an outer surface of the partition, and
wherein the reinforcement positioned in the outer diameter direction with respect to the central axis of the plurality of outer surface cooling holes is cylindrical, and the reinforcement positioned in the inner diameter direction with respect to the central axis of the plurality of outer surface cooling holes is rectangular.
6. The gas turbine blade according to claim 1 , wherein a distance between central axes of an adjacent outer surface cooling holes is equal to or more than a sum of a diameter of the at least one of the plurality of inner surface cooling holes and a width of the reinforcement in a position where the reinforcement intersects with the partition.
7. The gas turbine blade according to claim 1 , wherein the plurality of reinforcements have a cylindrical shape disposed coaxially with respect to the central axis of the plurality of outer surface cooling holes.
8. The gas turbine blade according to claim 1 , wherein the central axis of any or all of the outer surface cooling holes and the at least one of the plurality of inner surface cooling holes is inclined in the direction toward a trailing edge of the blade.
9. A gas turbine blade, comprising:
a cooling channel formed in the gas turbine blade;
a partition disposed on a tip side of the blade for isolating the cooling channel from an outside of the blade;
a tip end wall formed to extend from a tip of a blade portion toward the outside in a radial direction;
a plurality of reinforcements provided along a boundary between an outer surface of the partition and an inner surface of the tip end wall, the reinforcements being spaced apart from each other;
a plurality of outer surface cooling holes extending from the cooling channel into communication with an outer surface of the blade portion; and
a plurality of inner surface cooling holes extending from the cooling channel into communication with the inner surface of the tip end wall through the partition, wherein
an outer surface cooling hole is disposed to have a part superimposed over an arrangement area of a reinforcement when viewing the blade portion from the outside in the radial direction,
the outer surface cooling hole has an opening formed at an outer surface of the tip end wall,
the central axis of the plurality of outer surface cooling holes is positioned in an outer diameter direction with respect to a line of intersection of a surface forming an inner surface of the tip end wall and a surface forming an outer surface of the partition, and
the reinforcement positioned in the outer diameter direction with respect to the central axis of the plurality of outer surface cooling holes is cylindrical, and the reinforcement positioned in the inner diameter direction with respect to the central axis of the plurality of outer surface cooling holes is rectangular.