Method for mounting a gas turbine blade in an associated receiving recess of a rotor base body

Abstract

A gas turbine blade in an associated receiving recess of a rotor base body includes a slot in the blade root and has the shape of a straight cylinder. A blade retaining plate has a first securing region and a second securing region interconnected by a shaft region; the shaft region having the shape of a straight cylinder configured to conform to the slot of the blade root. The shaft region comes to rest on a bottom of the receiving recess of the rotor base body; the first securing region being reshaped to form a first limit stop for a first end wall of the blade root; and the second securing region being reshaped to allow the blade root to be inserted along the insertion direction into the receiving recess. The second securing region of the blade retaining plate is subsequently reshaped to allow the second securing region to form a second limit stop for a second end wall of the blade root facing opposite the first end wall, and the blade root to be secured in position in the receiving recess.

What it claimed is: 
     
         1 . A method for mounting a gas turbine blade in an associated receiving recess of a rotor base body, comprising the following steps:
 providing the gas turbine blade having a blade root, the turbine blade including a slot in the blade root, the slot extending along the blade root and having the shape of a straight cylinder whose longitudinal axis extends in parallel to a direction of insertion of the blade root into the receiving recess;   providing a blade retaining plate having a first securing region and a second securing region interconnected by a shaft region, the shaft region having the shape of a further straight cylinder configured to conform to the slot of the blade root;   configuring the blade retaining plate to allow the shaft region to come to rest on a bottom of the receiving recess of the rotor base body, the first securing region being reshaped to form a first limit stop for a first end wall of the blade root and the second securing region being reshaped to allow the blade root to be inserted along the insertion direction into the receiving recess;   inserting the blade root of the gas turbine blade along the insertion direction into the receiving recess of the rotor base body until the first end wall of the blade root rests against the limit stop formed by the reshaped first securing region, the shaft region of the blade retaining plate being configured within the slot of the blade root and filling the same when the first end wall comes to rest against the limit stop; and   reshaping the second securing region of the blade retaining plate to allow the second securing region to form a second limit stop for a second end wall of the blade root facing opposite the first end wall and the blade root to be secured in position in the receiving recess.   
     
     
         2 . The method as recited in  claim 1  wherein the slot in the blade root of the gas turbine blade is produced by the deposition and/or ablation of blade material. 
     
     
         3 . The method as recited in  claim 1  wherein at least one edge in the area of the slot of the blade root is rounded prior to placement of the shaft region of the blade retaining plate within the slot. 
     
     
         4 . The method as recited in  claim 1  wherein the blade root has at least one dovetail portion or at least one fir tree portion. 
     
     
         5 . A rotor for a gas turbine comprising:
 a rotor base body including at least one receiving recess;   a gas turbine blade having a blade root configured and secured in position in the at least one receiving recess by a blade retaining plate, the gas turbine blade including a slot in the blade root extending along the blade root and having the shape of a straight cylinder whose longitudinal axis extends in parallel to a direction of insertion of the blade root into the receiving recess;   the blade retaining plate having a first securing region and a second securing region interconnected by a shaft region, the shaft region having the shape of a further straight cylinder configured to conform to the slot of the blade root, the blade retaining plate being configured in the receiving recess in such a way that the shaft region thereof is configured within the slot of the blade root and fills the slot, the first securing region being reshaped to form a first limit stop for a first end wall of the blade root, and the second securing region being reshaped to allow the second securing region to form a second limit stop for a second end wall of the blade root facing opposite the first end wall.   
     
     
         6 . The rotor as recited in  claim 5  wherein the blade root and the shaft region of the blade retaining plate fill the receiving recess of the rotor base body completely, or the shaft region of the blade retaining plate is designed to conform to the slot of the blade root. 
     
     
         7 . The rotor as recited in  claim 5  wherein the blade root of the gas turbine blade is designed to be edge-free at least in the area of the slot thereof. 
     
     
         8 . A gas turbine comprising the rotor as recited in  claim 5 . 
     
     
         9 . An aircraft engine comprising the gas turbine as recited in  claim 8 . 
     
     
         10 . A gas turbine comprising at least one rotor including a rotor base body having at least one receiving recess in which a blade root of an associated gas turbine blade ( 14 ) is configured and secured in position by a blade retaining plate, wherein the gas turbine blade is mounted in the receiving recess of the rotor base body according to the method recited in  claim 1 . 
     
     
         11 . An aircraft engine comprising the gas turbine as recited in  claim 10 .