BLADE FOR GAS TURBINE, IMPLEMENTATION OF TURBINE BLADE AND PROCEDURE FOR TURBINE BLADE COOLING Russian patent published in 2010 - IPC F01D5/18 

FIELD: power engineering.

SUBSTANCE: gas turbine blade is made with wall of blade positioned on suction side and with wall of blade converging to it in area of back edge and positioned from pressure side. The blade wall positioned on the suction side consists of a neck of the back edge projecting at least at one separate section of the back edge area over the end edge of the blade wall positioned on the pressure side. Surface of the back edge neck positioned on the pressure side has recesses each equipped with a border correspondingly passing exceptionally in surface of the back edge neck positioned on the pressure side. The recesses have correspondingly elliptical, particularly, rounded border or a shape of ball segment.

EFFECT: increased efficiency of blade cooling due to local vortex of cooling air boosting heat transfer from back edge neck.

11 cl, 3 dwg