CERAMIC STATIONARY BLADE FOR GAS TURBINE

摘要

PROBLEM TO BE SOLVED: To resolve the occurrence of thermal stress at the rear end section of a mandrel insertion hole by providing multiple circular holes in the vertical direction at the rear half section of a ceramic blade section, i.e., the portion where no mandrel insertion hole is provided. ;SOLUTION: A ceramic stationary blade for a gas turbine is provided with ceramic blade sections 1..., a mandrel insertion hole 12 penetrating in the vertical direction is formed at the front half section of each blade section 1, a mandrel 4 is inserted into the mandrel insertion hole 12 via a heat insulating material 10, and cooling air holes 11... penetrating in the vertical direction are formed in the mandrel 4. Multiple circular holes 13 penetrating in the vertical direction are formed at a thick section behind the rear end section A of the mandrel insertion hole 12 of the blade section 1, cavities are formed in the thick section behind the section A, the thickness is practically reduced, and the heat capacity is reduced. The cooling speeds at the front and rear of the section A are made nearly equal at the time of a gas turbine trip, and the occurrence of cracks based on the thermal stress generated at the section A due to a temperature difference is prevented.;COPYRIGHT: (C)1997,JPO