Casting apparatus for producing a turbine rotor blade of a gas turbine and turbine rotor blade

Abstract

A casting apparatus for producing a turbine rotor blade of a gas turbine, and to a turbine rotor blade produced therewith is provided. The casting apparatus includes a hollow ceramic shell mold, of which the pouring gate and cores arranged therein are oriented with respect to each other such that a hot casting material flowing into a cavity of the ceramic shell mold does not come in direct contact with the cores. Thus, so-called hot spots on cores are avoided, which until now have had negative effects on the solidification of the casting material. Especially in the region of the blade root of the turbine rotor blade to be produced improved solidification of the casting material may thus be obtained, reducing any disturbance in the structure of the solidified casting material.

1 - 6 . (canceled) 
     
     
         7 . A casting apparatus for producing a turbine rotor blade of a gas turbine, comprising:
 a hollow mold shell, a cavity of which is delimited by a surface and represents a negative mold of the turbine rotor blade to be produced;   one or more casting cores arranged in the cavity; and   an inlet channel for a casting material, including an inlet opening which issues into the surface,   wherein the surface is oriented in the mold shell in such a manner that a blade root of the turbine rotor blade to be cast is contoured on an inlet side,   wherein the surface for the blade root of the turbine rotor blade has a symmetrical contour in the form of a fir tree or hammer on both sides of a blade root center, and   wherein the inlet channel includes a longitudinal extent immediately upstream of the inlet opening thereof, and   wherein the inlet channel is arranged centrally between the blade root contour which is in the form of a fir tree or hammer, one of the casting cores is arranged on the inlet opening side, but eccentrically, such that that part of the cavity into which an imaginary beam-like extension of the inlet channel protrudes is free of casting cores at least on the inlet opening side.   
     
     
         8 . The casting apparatus as claimed in  claim 9 ,
 wherein the inlet channel issues into that part of the surface which fauns the negative of a planar end face of the blade root of the turbine rotor blade.   
     
     
         9 . The casting apparatus as claimed in  claim 9 , further comprising a plurality of casting cores arranged at least in a region of the inlet opening on both sides of the blade root center. 
     
     
         10 . The casting apparatus as claimed in  claim 9 , wherein that part of the cavity into which an imaginary extension of the inlet channel protrudes is completely free of casting cores. 
     
     
         11 . A turbine rotor blade for a gas turbine, comprising:
 a blade root, along a longitudinal axis thereof, in the form of a fir tree or in the form of a hammer in longitudinal section;   a platform; and   an aerodynamically curved main blade part adjoining the platform,   wherein the blade root is formed symmetrically with respect to the longitudinal axis of the turbine rotor blade on both sides of a blade root center, and an underside thereof, which faces away from the main blade part and runs transversely to the longitudinal axis, includes one or more openings for the introduction of a coolant, and   wherein at least one opening is arranged eccentrically.   
     
     
         12 . The turbine rotor blade as claimed in  claim 13 , wherein two openings are arranged on both sides of the blade root center. 
     
     
         13 . The turbine rotor blade as claimed in  claim 13 ,
 wherein the blade root of which includes two planar end faces at opposite ends from one another, and   wherein at least two openings lying in series and each arranged eccentrically are provided between the end faces.   
     
     
         14 . The turbine rotor blade as claimed in  claim 13 , wherein each opening forms an end of a cooling channel of the turbine rotor blade.