Turbine blade, manufacturing method of turbine blade, and strip judging method of thermal barrier coat

Abstract

There is disclosed a turbine blade comprising a turbine blade main body 10 with a blade-shaped section and a thermal barrier coat 20 as an insulating layer. The turbine blade main body 10 includes an internal air gap 12 disposed inside so that a coolant gas passes and a plurality of coolant gas ports 13 connected to the internal air gap and disposed in the outer peripheral surface. The thermal barrier coat 20 is coated with the outer peripheral surface of the turbine blade main body. The thermal barrier coat fills in at least some of the coolant gas ports. Thereby, a temperature of a high-temperature gas is raised and the turbine blade can be run.

1 . A turbine blade ( 2 ) which outer peripheral surface has a blade shape, comprising: 
 a turbine blade main body ( 10 ) with a blade-shaped section including an internal air gap ( 12 ) disposed inside so that a coolant gas passes and a plurality of coolant gas ports ( 13 ) disposed in the outer peripheral surface so that the ports can be connected to the internal air gap; and    a thermal barrier coat ( 20 ) as an insulating layer with which the outer peripheral surface of the turbine blade main body is coated,    wherein said thermal barrier coat fills in at least some of said coolant gas ports.    
     
     
         2 . The turbine blade according to  claim 1  wherein said thermal barrier coat ( 20 ) fills in the coolant gas ports the number of which exceeds 20% of the total number of coolant gas ports ( 13 ).  
     
     
         3 . A manufacturing method of a turbine blade ( 2 ) which outer peripheral surface has a blade shape, the method comprising: 
 a turbine blade main body preparing step (A) for preparing a turbine blade main body ( 10 ) with a blade-shaped section including an internal air gap ( 12 ) disposed inside so that a coolant gas passes and a plurality of coolant gas ports ( 13 ) disposed in the outer peripheral surface so that the coolant gas ports can be connected to the internal air gap;    a sealing step (B) for filling a sealer into at least some of said coolant gas ports; and    a coating step (C) for disposing an insulating layer on an outer surface of the turbine blade main body after the sealing step.    
     
     
         4 . The manufacturing method of the turbine blade according to  claim 3  wherein said sealing step (B) comprises: a step for filling the sealer into the coolant gas ports the number of which exceeds 20% of the total number of said coolant gas ports.  
     
     
         5 . The manufacturing method of the turbine blade according to  claim 3  or  4 , further comprising: a sealer removing step (D) of removing the sealer after said coating step (C).  
     
     
         6 . A strip judging method of a thermal barrier coat, comprising steps for: 
 preparing a turbine using the turbine blade ( 2 ) according to  claim 1  or  2 ;    detecting consumption of a coolant gas supplied to the turbine blade; and    judging the presence of a strip of said thermal barrier coat ( 20 ) by a fluctuation of said consumption.