Axial turbomachine rotor having blade cooling

Abstract

An axial turbomachine rotor is provided. The rotor includes a rotor disk and a rotor blade ring, which includes a plurality of rotor blades, each of which include a blade root, with which the rotor blade is fixed radially outward on the rotor disk, wherein the blade root is engaged with the rotor disk at the outer edge of the rotor disk in a form-closed manner in such a way that during operation of the rotor, a gap is formed between the rotor blade and the rotor disk at a predetermined surface area of the rotor disk, in which area, a plurality of impingement cooling openings is arranged, through which a cooling medium may flow from the interior of the rotor disk into the gap whereby the rotor blade is cooled using the cooling medium by means of impingement cooling.

1 .- 9 . (canceled) 
     
     
         10 . An axial turbomachine having a rotor disk and a rotor blade ring, comprising:
 a plurality of rotor blades, each including a blade root by which the rotor blade is fixed radially outwards on the rotor disk; and   a plurality of impingement-cooling openings,   wherein the blade root engages with the rotor disk on an outer edge of the rotor disk in a form-fitting manner in such a way that during operation of the axial turbomachine rotor, a gap is formed between the rotor blade and the rotor disk in a predetermined surface region of the rotor disk, and   wherein in the gap are arranged the plurality of impingement-cooling openings through which a cooling medium may flow from an interior of the rotor disk into the gap, as a result of which the rotor blade is cooled by the cooling medium by means of impingement cooling and the rotor disk is cooled by the cooling medium by means of convective cooling.   
     
     
         11 . The axial turbomachine rotor as claimed in  claim 10 ,
 wherein the rotor disk, on its outer edge, includes a retaining recess, in which the blade root engages by its root neck which projects radially inwards and includes a root tooth which projects from the root neck in a circumferential direction and/or in the axial direction and includes a radially outer flank and a radially inner flank,   wherein the root tooth is encompassed by a root tooth recess which is provided in the retaining recess in such a way that during operation of the turbomachine rotor the blade root bears by the radially outer flank against the root tooth recess and a first gap is formed between the radially inner flank and the root tooth recess, and   wherein in a surface region of the root tooth recess facing the inner flank provision is made for a first impingement-cooling opening so that the blade root may be impingement-cooled on the radially inner flank by the cooling medium which flows through the first impingement-cooling opening.   
     
     
         12 . The axial turbomachine rotor as claimed in  claim 11 ,
 wherein the root tooth is arranged and formed on the root neck in such a way that the blade root includes a firtree profile, and   wherein the root tooth recess is formed as a groove.   
     
     
         13 . The axial turbomachine rotor as claimed in  claim 12 , wherein the root tooth and the groove extend in the axial direction. 
     
     
         14 . The axial turbomachine rotor as claimed in  claim 10 , wherein the gap is outwardly open so that the cooling medium may flow from the gap to outside the rotor disk. 
     
     
         15 . The axial turbomachine rotor as claimed in  claim 10 ,
 wherein the rotor blade includes an aerodynamically effective blade airfoil and an aerodynamically effective blade platform which is arranged radially between the blade airfoil and the blade root and by its radially inner side is arranged at a radial distance from the outer edge of the rotor disk, forming a second gap, and   wherein in a surface region of the outer edge facing an inner side provision is made for a second impingement-cooling opening so that the blade platform may be impingement-cooled on its radially inner side by the cooling medium which flows through the second impingement-cooling opening.   
     
     
         16 . The axial turbomachine rotor as claimed in  claim 10 , wherein the plurality of impingement-cooling openings are formed in such a way that the cooling medium, which flows out of the impingement-cooling openings, impinges essentially perpendicularly upon a surface of the rotor blade. 
     
     
         17 . The axial turbomachine rotor as claimed in  claim 15 , wherein the rotor disk includes a plurality of cooling passages which open out into the second gap via the second impingement-cooling opening. 
     
     
         18 . The axial turbomachine rotor as claimed in  claim 10 , wherein the rotor disk includes a plurality of cooling passages which open out into the gap via the plurality of impingement-cooling openings. 
     
     
         19 . The axial turbomachine rotor as claimed in  claim 10 , wherein the axial turbomachine rotor is an axial turbine rotor and the cooling medium is cooling air. 
     
     
         20 . The axial turbomachine rotor as claimed in  claim 15 , wherein the axial turbomachine rotor is an axial turbine rotor and the cooling medium is cooling air.