TURBINE BLADE Russian patent published in 2018 - IPC F01D5/28 

FIELD: machine building.

SUBSTANCE: turbine blade comprises a cooling channel which is formed in the blade and extends in the height direction thereof, and a plurality of cooling holes. Suction side and pressure side of the blade are covered with a heat-shielding coating. Design point on the suction side is set on the blade surface on the suction side in each section of the blade, perpendicular to the direction of the blade height, within the range from the position behind the critical section position, including this position in which the distance between the turbine blades is minimum, up to the position in front of the position of the outlet end of the last cooling channel, except for this position which is closest to the trailing edge of the blade. Distribution of the thickness of the heat-shielding coating on the suction side of each section of the blade is such that the thickness of the heat-shielding coating is constant from the leading edge of the blade to the design point and gradually decreases from the design point back to the trailing edge of the blade. Plurality of cooling holes for forming a film on the suction side are formed in the blade surface and the heat-shielding coating on the suction side and communicate with the cooling channel. Cooling holes for forming a film on the suction side in the last plurality nearest to the trailing edge of the blade from the plurality of cooling holes to form a film, on the suction side are present within the range from behind the critical section position and including this position, and to the position in front of the position of the outlet end of the last cooling channel and with the exception of this position. Design point is set within a range from the position behind the position of the cooling holes for forming a film on the suction side in the last plurality and including this position, and up to the position in front of the position of the outlet end of the last cooling channel and with the exception of this position on the blade surface on the suction side in each section of the blade.

EFFECT: invention improves the aerodynamic characteristics of the airfoil.

3 cl, 8 dwg