Turbine rotor blade of gas turbine engine, has overhang which is provided at stagnation point, when intersection point is zero, so that maximum value of barrel length of suction-side overhang is at about specific percentage

摘要

The rotor blade has a blade tip which is provided with a suction side that is started from a stagnation point on the blade leading edge to a point of intersection of the suction-side profile line of the vane (24) that is provided with a trailing edge circle. An overhang (30) is provided at the stagnation point, when intersection point is zero, so that maximum value of the barrel length of the suction-side overhang is at about 40%. The suction-side overhang is formed in the region of the narrowest cross section of the blade passage.