Patent ID: 6318960
Filing Date: 2001-11-20
Classification: F01D,F05D

Abstract:
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 the inserts has a multiplicity of air blowing holes 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 the first group of air blowing holes has a diameter that is larger than each hole of the second group of air blowing holes, and the first group of air blowing holes is provided in a dorsal side rear portion of the insert that is located at the leading edge side of the blade, andwherein a plurality of cooling holes are provided in the blade, each of the cooling holes that are 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.