Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine

Abstract

A restraint mechanism for rotor blades of a turbo engine on a rotor disk having blade root receptacles for radial guidance of the rotor blades is disclosed. The restraint mechanism has a plurality of axial securing elements, each having at least one web for positioning in a blade root receptacle, such that each web has a retaining section at one end for establishing a form-fitting design to a mating brace of another axial securing element. A method for axially securing rotor blades on a rotor disk and a turbo engine are also disclosed.

What is claimed is: 
     
         1 . A restraint mechanism for rotor blades of a turbo engine on a rotor disk, comprising:
 a plurality of axial securing elements, wherein each of the plurality of axial securing elements has at least one web for positioning in a respective blade root receptacle of the rotor disk, wherein the at least one web has a retaining section at a first end and a mating brace at a second end, and wherein the retaining section of one of the plurality of axial securing elements connects to the mating brace of an opposite one of the plurality of axial securing elements.   
     
     
         2 . The restraint mechanism according to  claim 1 , wherein the retaining section is narrower than the respective blade root receptacle and has both an installation position and a securing position. 
     
     
         3 . The restraint mechanism according to  claim 1 , wherein the mating brace is offset in a vertical direction of the axial securing element and has an elongated shape extending in a transverse direction of the axial securing element, and wherein the mating brace has an extent such that, when installed, the mating brace extends over at least one neighboring blade root receptacle. 
     
     
         4 . The restraint mechanism according to  claim 3 , wherein two of the plurality of axial securing elements form a securing element pair and wherein the respective mating braces of the two axial securing elements extend in the transverse direction on one end of the respective axial securing element. 
     
     
         5 . The restraint mechanism according to  claim 3 , wherein two of the plurality of axial securing elements form a securing element pair, wherein the mating brace of a first of the two axial securing elements extends on both sides of the respective at least one web, and wherein the mating brace of a second of the two axial securing elements extends between the respective at least one web and a second web of the second of the two axial securing elements. 
     
     
         6 . The restraint mechanism according to  claim 3 , wherein at least one of the plurality of axial securing elements has a second web, wherein the respective mating brace of the at least one of the plurality of axial securing elements extends between the at least one web and the second web, and wherein the respective at least one web of two opposite axial securing elements of the plurality of axial securing elements are disposed between the at least one web and the second web of the at least one of the plurality of axial securing elements. 
     
     
         7 . The restraint mechanism according to  claim 6 , wherein at least one of the plurality of axial securing elements is an I-shaped axial securing element, wherein the I-shaped axial securing element does not have a mating brace and has a body section that is wider than a respective blade root, and wherein the I-shaped axial securing element is disposed between the at least one web and the second web of the at least one of the plurality of axial securing elements. 
     
     
         8 . The restraint mechanism according to  claim 1 , wherein the retaining section has a catch nose and wherein the catch nose connects to the mating brace of the opposite one of the plurality of axial securing elements. 
     
     
         9 . A method for axially securing rotor blades on a rotor disk of a turbo engine, comprising the steps of:
 inserting respective blade roots of the rotor blades into respective axial blade root receptacles of the rotor disk; and   inserting securing elements which are connected to one another by at least a form-fitting connection into the blade root receptacles.   
     
     
         10 . The method according to  claim 9 , wherein the securing elements are connected to one another by a mutual form-fitting design. 
     
     
         11 . A turbo engine, comprising:
 a bladed rotor disk, wherein blades of the bladed rotor disk are secured axially by a restraint mechanism according to  claim 1 .   
     
     
         12 . A restraint mechanism for rotor blades of a turbo engine on a rotor disk, comprising:
 a first axial securing element, wherein the first axial securing element has a first web, a first retaining section at a first end of the first web, and a first mating brace at a second end of the first web, wherein the first web is positioned in a first blade root receptacle of the rotor disk, and wherein the first retaining section is disposed on a first side of the rotor disk and the first mating brace is disposed on a second side of the rotor disk; and   a second axial securing element, wherein the second axial securing element has a second web, a second retaining section at a first end of the second web, and a second mating brace at a second end of the second web, wherein the second web is positioned in a second blade root receptacle of the rotor disk, and wherein the second retaining section is disposed on the second side of the rotor disk and the second mating brace is disposed on the first side of the rotor disk;   wherein the first blade root receptacle is adjacent to the second blade root receptacle;   wherein the first side of the rotor disk is opposite from the second side of the rotor disk;   wherein the first retaining section of the first axial securing element disposed on the first side of the rotor disk is connected to the second mating brace of the second axial securing element disposed on the first side of the rotor disk;   and wherein the second retaining section of the second axial securing element disposed on the second side of the rotor disk is connected to the first mating brace of the first axial securing element disposed on the second side of the rotor disk.