Moving blade for a turbomachine, the blade having a common cooling air feed cavity

Abstract

A moving blade for a turbomachine, the blade comprising an aerodynamic surface extending radially between a blade root and a blade tip, and at least one internal cooling circuit made up of at least one radial cavity, at least one air admission opening formed in the blade root and opening out into the cavity(ies), and a plurality of outlet orifices opening out from the cavity(ies) and leading to the outside of the blade, the blade root having lower swellings and upper swellings defining bearing surfaces for fastening the blade to a rotor disk. The air admission openings of the cooling circuit(s) open out into a common cavity that is formed in the blade root and that extends radially from the base of the blade root at least as far as the upper swelling of said root.

1 . A moving blade for a turbomachine, the blade comprising an aerodynamic surface extending radially between a blade root and a blade tip, and at least one internal cooling circuit made up of at least one radial cavity, at least one air admission opening formed in the blade root and opening out into the cavity(ies), and a plurality of outlet orifices opening out from the cavity(ies) and leading to the outside of the blade, the blade root having lower swellings and upper swellings defining bearing surfaces for fastening the blade to a rotor disk, wherein the air admission openings of the cooling circuit(s) open out into a common cavity that is formed in the blade root and that extends radially from the base of the blade root at least as far as the upper swelling of said root. 
   
   
       2 . A blade according to  claim 1 , wherein the common cavity has keying means for ensuring that a plate for calibrating the flow rates of air fed to the cavities of the cooling circuit(s) cannot be installed the wrong way round. 
   
   
       3 . A blade according to  claim 1 , wherein the common cavity is open in part through an upstream wall so as to facilitate feeding air to said common cavity. 
   
   
       4 . A blade according to  claim 1 , wherein the end wall of the common cavity is inclined from upstream to downstream relative to the base of the blade root in such a manner as to facilitate feeding air to said common cavity. 
   
   
       5 . A blade according to  claim 1 , wherein said common cavity includes a radial wall forming a stiffener disposed so as to subdivide the cavity into at least two sub-cavities. 
   
   
       6 . A turbomachine high-pressure turbine, including a plurality of moving blades according to  claim 1 . 
   
   
       7 . A turbomachine, including a plurality of moving blades according to  claim 1 .