GAS TURBINE BLADES WITH AN END SECTION SHIFTED TOWARDS THE HIGH PRESSURE AND COOLING CHANNELS Russian patent published in 2017 - IPC F01D5/18 F01D5/20 

FIELD: machine engineering.

SUBSTANCE: hollow blade has an airfoil section extending in a longitudinal direction and comprises a base, an end, an internal cooling channel within the airfoil section, a cavity located at the end open to the free blade end and bounded by the end wall and the rim. The rim is extending between the leading and the trailing edges and includes a low pressure side of the rim along the low pressure side and high pressure sides of the rim along the high pressure side, and cooling channels connecting the said internal cooling channel from the high pressure side. The cooling channels are inclined with respect to the high pressure side. Laying of aerodynamic blade sections at the blade end rim level is offset towards the high pressure side, increasing when approaching the free blade end. The wall of the high pressure side of the airfoil section is a projecting portion, more than half of its length extends along the longitudinal portion of the inner cooling channel, and the outer surface of which is inclined with respect to the rest of the high pressure side of the airfoil section, and having an end surface at its end facing the cavity. The end wall is connected to the hight pressure side wall in the area of the protruding section end. The cooling channels are arranged in the projecting section to open in the end surface of the protruding section, whereby the distance between the cooling channels axes and their outer limit of the high pressure side free end is more than or equal to the minimum nonzero value.

EFFECT: development of the blade design, which makes it possible to maintain the high efficiency of the cooling system of the blade top, even when the blade has an improved top of end sections spaced type.

15 cl, 11 dwg