Gas turbine stationary blade

A gas turbine stationary blade assembly constructed such that a blade is fixed to an outer shroud and an inner shroud and a plurality of passages are provided in the blade, a generally cylindrical insert being inserted in each of said passages so that a predetermined spacing is maintained from an inner wall of the respective passage, wherein each of said inserts has a multiplicity of air blowing holes, wherein a leading edge of the blade has a curved surface formed on an elliptical curve at an ellipse long axis, and

• wherein the leading edge portion of the blade defines a projection having a curved surface formed on an elliptical curve at an ellipse long axis, the projection having a plurality of cooling holes,
• a plurality of fillets connecting portions of the blade to the outer shroud and the inner shroud, each of the fillets having curved surfaces formed on an elliptical curve at an ellipse short axis,
• wherein each of the inserts is supported at two locations in the respective passage, and one of the inserts is provided on a leading edge side of the blade and includes a first group of air blowing holes and a second group of air blowing holes,
• wherein each hole of said first group of the air blowing holes has a diameter that is larger than each hole of said second group of the air blowing holes, and the first group of air blowing holes is provided in a dorsal side rear portion of the insert in the leading edge side of the blade, and a plurality of cooling holes are provided in the blade, each of the cooling holes provided in a dorsal portion of the blade near said first group of the air blowing holes has a diameter that is larger than the other cooling holes.

A gas turbine stationary blade comprising:

• a blade section having a surface defined by a first portion and a second portion;
• a first passage provided in a leading edge side of said blade section;
• a second passage provided in a trailing edge side of said blade section;
• a first insert mounted in said first passage, said first insert having a plurality of air blowing holes defining a first group of air blowing holes and a second group of air blowing holes, wherein said air blowing holes of said first group are provided in a dorsal side rear portion of said first insert and have larger diameters than said air blowing holes of said second group;
• a second insert mounted in said second passage;
• and
• a plurality of cooling holes provided in said first and second surface portions of said blade, wherein said first surface portion is located near said first group of air blowing holes, and each of said cooling holes provided in said first surface portion has a diameter that is larger than said cooling holes provided in said second surface portion.

A gas turbine stationary blade assembly comprising:

• a blade disposed between an inner shroud and an outer shroud;
• a plurality of fillets connecting said blade to said inner and outer shrouds, wherein each of said fillets has a curved surface defined by a portion of an elliptical curve at an ellipse short axis;
• a first passage provided in a leading edge section of said blade and a second passage provided in a trailing edge section of said blade;
• a first insert mounted at only two places in said first passage, said first insert having a plurality of air blowing holes defining a first group of air blowing holes and a second group of air blowing holes, wherein each of said air blowing holes of said first group is provided in a dorsal side rear portion of said first insert and has a diameter that is larger than each of said air blowing holes of said second group;
• and
• a plurality of cooling holes provided in said blade, wherein a number of said cooling holes, which are located near said first group of air blowing holes of said first insert, each has a diameter that is larger than the other of said cooling holes,
• wherein a leading edge portion of said blade defines a projection having a curved surface that is defined by a section of an elliptical curve at an ellipse long axis.