Gas turbine blade assembly having retainer assembling structure, and gas turbine having same

Abstract

A gas turbine blade assembly, which is as an assembly provided with a plurality of gas turbine blades on an outer circumferential surface of a rotating disk along a circumferential direction to be spaced apart from each other at predetermined intervals, includes: a retainer insertion hole provided in a blade-fixing end, and depressed by a predetermined depth to correspond to a lower end of a retainer; a retainer coupler provided at a lower end of each of the gas turbine blades, and depressed by a predetermined depth to correspond to an upper end of the retainer; and a coupling member coupled at a location adjacent to the retainer coupler to couple the retainer and each of the gas turbine blades together.

What is claimed is: 
     
         1 . A gas turbine blade assembly, comprising:
 a turbine blade including a retainer coupler provided a first distance from a first end;   a rotating disk including a blade-fixing end and a retainer insertion hole defined in the blade-fixing end, a depth of the retainer insertion hole being at least the first distance;   a retainer sized to be disposed in the retainer insertion hole; and   a coupling member disposed at a location proximal to the retainer coupler to couple the retainer and the turbine blade together.   
     
     
         2 . The gas turbine blade assembly of  claim 1 , wherein
 the rotating disk includes a dovetail slot on an outer circumferential surface,   the turbine blade is operable to mount to the dovetail slot, and   the turbine blade is aligned in an axial direction by the retainer.   
     
     
         3 . The gas turbine blade assembly of  claim 1 , wherein the rotating disk includes a protruding structure at an upper surface providing the retainer insertion hole. 
     
     
         4 . The gas turbine blade assembly of  claim 3 , wherein the protruding structure is disposed along a circumferential direction of the rotating disk, and is in an annular shape in a plan view. 
     
     
         5 . The gas turbine blade assembly of  claim 1 , wherein an inner surface of the retainer insertion hole includes a bearing surface operable to contact the retainer. 
     
     
         6 . The gas turbine blade assembly of  claim 1 , wherein
 a lower end of the retainer is spaced apart from a bottom surface of the retainer insertion hole, and   a depth of the retainer coupler is equal to or less than the distance between the lower end of the retainer and the bottom surface of the retainer insertion hole.   
     
     
         7 . The gas turbine blade assembly of  claim 1 , further comprising a coupling member insertion hole defined at a location adjacent to the retainer coupler at the first end of the turbine blade. 
     
     
         8 . The gas turbine blade assembly of  claim 7 , wherein a slot groove in a shape corresponding to an outer surface of the coupling member is defined between the coupling member insertion hole and the retainer coupler. 
     
     
         9 . The gas turbine blade assembly of  claim 8 , wherein the slot groove is disposed in a direction parallel to an extension direction of the retainer. 
     
     
         10 . The gas turbine blade assembly of  claim 7 , wherein the coupling member includes a bolt, a head of the bolt head being disposed proximal to the coupling member insertion hole, and a threaded part of the bolt protruding in a direction toward the retainer coupler to engage with the retainer. 
     
     
         11 . The gas turbine blade assembly of  claim 10 , wherein
 the threaded part of the coupling member is operable to engage with a nut to couple the coupling member and the retainer together, and   an outer surface of the nut includes a curved surface corresponding to an outer surface of an end of the turbine blade.   
     
     
         12 . The gas turbine blade assembly of  claim 1 , wherein the first end of the turbine blade includes a sealing protrusion that protrudes toward a neighboring gas turbine blade. 
     
     
         13 . The gas turbine blade assembly of  claim 12 , wherein the retainer includes an auxiliary sealing protrusion that protrudes by a length to corresponding to a length of the sealing protrusion. 
     
     
         14 . The gas turbine blade assembly of  claim 1 , wherein
 a side surface of the retainer includes a support protrusion extending in a direction toward the first end of the turbine blade,   the retainer includes and a contact surface corresponding to a side surface of the turbine blade, and   a sealing wire is disposed on the contact surface of the support protrusion.   
     
     
         15 . A gas turbine comprising:
 a blade assembly including a plurality of gas turbine blades on an outer circumferential surface of a rotating disk along a circumferential direction and spaced apart from each other, wherein the blade assembly includes:   a retainer coupler provided a first distance from a first end of one of the turbine blades;   a retainer insertion hole defined in a blade-fixing end of the rotating disk, a depth of the retainer insertion hole being at least the first distance;   a retainer sized to be disposed in the retainer insertion hole; and   a coupling member disposed at a location proximal to the retainer coupler to couple the retainer and the turbine blade together.   
     
     
         16 . The gas turbine of  claim 15 , wherein
 the rotating disk includes a protruding structure at an upper surface providing the retainer insertion hole.   
     
     
         17 . The gas turbine of  claim 16 , wherein the protruding structure is disposed along a circumferential direction of the rotating disk, and is in an annular shape in a plan view. 
     
     
         18 . The gas turbine of  claim 15 , wherein
 a lower end of the retainer is spaced apart from a bottom surface of the retainer insertion hole, and   a depth of the retainer coupler is equal to or less than the distance between the lower end of the retainer and the bottom surface of the retainer insertion hole.   
     
     
         19 . The gas turbine of  claim 15 , further comprising a coupling member insertion hole defined at a location adjacent to the retainer coupler at the first end of the turbine blade.