TURBOMACHINE COOLED BLADE Russian patent published in 2009 - IPC F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: turbomachine cooled blade incorporates blade airfoil portion with cavity and its front edge cooling channel communicating, via inlet and outlet channels alternating over its length, with blade airfoil portion cavity and ambient atmosphere, respectively. Outlet channels represent tangential ports relative to blade airfoil portion front edge cooling channel. Inlet channel lengthwise axes are directed tangentially to midlines of the blade airfoil portion flat profiles, within the limits of front edge cooling channel. Rear edges of inlet channels are brought out into front edge cooling channel so that distance L, measured along inlet channel lengthwise axis, from inlet channel rear edge to opposite front edge cooling channel rear edge, makes 0.85 to 1.65 of the mean radius of curvature R_mean. Of the said channel wall section and relates with equivalent inlet channel diametre d_{in. channel} by the following expression, i.e. 2.5>L/ d_{in. channel} >0.9.

EFFECT: efficient cooling of blade airfoil portion front edge.

2 dwg, 2 cl