Turbomachine having axial rotor blade securing

Abstract

A rotor of a turbine machine having several rotor blade rings positioned in succession in the axial direction, is disclosed. Each rotor blade ring has a rotor base body with several rotor blades anchored by blade footings in axial grooves of the rotor base body that extend essentially in the axial direction and, in their anchored position in the rotor base body, are secured against displacement in the axial direction. The rotor blades of at least one rotor blade ring have hook-like securing elements, which, in the anchored position on a low-pressure side of the rotor blade ring, abut the rotor base body. The hook-like securing elements, between the rotor base body and a sealing element, which extends between the rotor base body and a rotor base body of a rotor blade ring that connects on the low-pressure side, are fixed in the axial direction on both sides.

1 - 7 . (canceled) 
   
   
       8 . A turbomachine having several rotor blade rings positioned in succession in an axial direction that are assigned to a turbine or a compressor, wherein each rotor blade ring has a rotor base body with several rotor blades, and wherein the rotor blades of a rotor blade ring are anchored by respective blade footings in axial grooves of a rotor base body of the rotor blade ring that extend in the axial direction and, in an anchored position in the rotor base body, are secured against displacement in the axial direction, and wherein the rotor blades of at least one rotor blade ring have a hook-like securing element, which, in the anchored position on a low-pressure side of the rotor blade ring, abut the rotor base body, wherein the hook-like securing element between the rotor base body of the rotor blade ring and a sealing element, which extends between the rotor base body and a rotor base body of a rotor blade ring that connects on the low-pressure side, are fixed in the axial direction on both sides. 
   
   
       9 . The turbomachine according to  claim 8 , wherein the hook-like securing element between the rotor base body of the rotor blade ring and the sealing element is clamped in the axial direction on both sides. 
   
   
       10 . The turbomachine according to  claim 8 , wherein the sealing element is fastened bayonet-like via a section adjacent to the hook-like securing element on the rotor base body of the rotor blade ring. 
   
   
       11 . The turbomachine according to  claim 10 , wherein the section of the sealing element fixes the hook-like securing element of the rotor blade in the axial direction on both sides. 
   
   
       12 . The turbomachine according to  claim 10 , wherein the section of the sealing element has a projection, which is insertable via an opening into a groove of the rotor base body in the axial direction, wherein the sealing element is rotatable in a circumferential direction following the bayonet-like fastening of same. 
   
   
       13 . The turbomachine according to  claim 8 , wherein the sealing element is fastened via a projection between a flange of the rotor base body and a flange of the rotor base body of the rotor blade ring that connects on the low-pressure side. 
   
   
       14 . The turbomachine according to  claim 13 , wherein a section of the sealing element adjacent to the projection fixes the hook-like securing element of the rotor blades in the axial direction on both sides. 
   
   
       15 . A turbomachine, comprising:
 a rotor blade ring having a rotor blade and a rotor base body, wherein the rotor blade is anchored in an axial groove of the rotor base body;   and wherein the rotor blade includes a hook-like securing element which is secured between the rotor base body and a sealing element which extends between the rotor base body and a second rotor base body of a second rotor blade ring.   
   
   
       16 . The turbomachine according to  claim 15 , wherein the hook-like securing element extends in a radially inward direction of the rotor blade ring. 
   
   
       17 . The turbomachine according to  claim 15 , wherein the hook-like securing element is disposed on a low-pressure side of the rotor blade and wherein a portion of the hook-like securing element extends beyond a radially inner end of the rotor blade. 
   
   
       18 . The turbomachine according to  claim 15 , wherein the sealing element includes a section that is fastened bayonet-like on the rotor base body. 
   
   
       19 . The turbomachine according to  claim 18 , wherein the section abuts the hook-like securing element. 
   
   
       20 . The turbomachine according to  claim 18 , wherein the section has a projection which is insertable into a groove of the rotor base body. 
   
   
       21 . The turbomachine according to  claim 15 , wherein the sealing element includes a projection that is fastened between a flange of the rotor base body and a flange of the second rotor base body. 
   
   
       22 . The turbomachine according to  claim 15 , further comprising a guide vane ring disposed between the rotor blade ring and the second rotor blade ring. 
   
   
       23 . The turbomachine according to  claim 22 , wherein the guide vane ring includes a seal and wherein the sealing element engages with the seal. 
   
   
       24 . The turbomachine according to  claim 23 , wherein the seal is a brush seal. 
   
   
       25 . The turbomachine according to  claim 23 , wherein the seal seals a radial inner gap defined by the rotor blade rings and the guide vane ring. 
   
   
       26 . The turbomachine according to  claim 15 , wherein the hook-like securing element which is secured between the rotor base body and a sealing element is fixed in an axial direction of the turbomachine.