Blade comprising an improved cooling circuit

#This application is the U.S. national phase entry under 35 U.S.C. § 371 of International Application No. PCT/FR2018/000079, filed on Apr. 10, 2018, which claims priority to French Patent Application No. 1700388, filed on Apr. 10, 2017.

#The present disclosure relates to a blade, for example a blade for a turbine that can be used within an aircraft turbomachine, and more particularly to the internal cooling of such a blade.

#An aircraft turbomachine usually comprises a combustion chamber whose combustion gases rotatably drive one or more turbines. To protect the turbine blades from the high temperatures to which they are thus subjected, particularly the movable blades, it is known to provide that the blades are hollow so as to make a coolant, for example relatively cold air taken upstream of the combustion chamber, circulate inside the blades.

#The invention and its advantages will be better understood upon reading the following detailed description, of embodiments of the invention given as non-limiting examples. This description refers to the appended drawings, wherein:

#FIG. 1 represents, in perspective, a blade for a turbine according to a first embodiment;

#FIG. 2 represents the blade according to the first embodiment in cross-section along the plane II-II of FIG. 1;

#FIG. 1 represents, in perspective, an example of a hollow rotor blade 10 for a gas turbine, according to a first embodiment. Cooling air (not represented) flows inside the blade from the bottom of the root 12 of the blade into the airfoil 13, along the longitudinal direction R-R′ of the airfoil 13 (vertical direction in the figure and radial direction with respect to the axis of rotation X-X′ of the rotor), towards the tip 14 of the blade (at the top in FIG. 1), then this cooling air escapes through an outlet to join the main gas stream. The root 12 forms the radially inner end of the blade 10 and the tip 14 forms the radially outer end of the blade 10.

#Particularly, this cooling air circulates in an internal cooling circuit which is located inside the airfoil 13 and some branches of which lead to the tip 14 of the blade at through bores 15 provided in a tub.

#The body of the airfoil is profiled so that it defines an intrados wall 16 and an extrados wall 18. The intrados wall 16 has a generally concave shape and is the first one appearing facing the hot gas stream that is to say on the pressure side of the gases, through its external face, oriented upstream. The extrados wall 18 is convex and appears subsequently facing the hot gas stream that it is to say on the suction side of the gases, along its external face, oriented downstream.