Patent ID: 11939881
Assignee: MITSUBISHI ELECTRIC CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A gas turbine rotor blade comprising:
a base end portion fixed to a rotor;
a blade-shaped portion extending in a radial direction of the rotor and having a pressure-side blade surface and a suction-side blade surface, the blade surfaces forming a blade shape between a leading edge and a trailing edge of the blade-shaped portion; and
a platform provided between the base end portion and the blade-shaped portion, wherein
the platform includes a groove portion recessed from an end surface on the trailing edge side toward the leading edge side and extending in a circumferential direction of the rotor,
a bottom portion of the groove portion overlaps at least the blade-shaped portion when viewed from the radial direction,
when a pressure-side end portion of the platform with respect to the bottom portion is defined as a first point, a tangent line that is a tangent line of the bottom portion at the first point and extends along a plane intersecting the radial direction is defined as a first tangent line,
when an intersection between a line segment connecting the bottom portion and an end portion on the trailing edge side of a serpentine cooling flow path provided inside the blade-shaped portion when viewed from the radial direction and an end portion on the trailing edge side of the blade-shaped portion is defined as a second point, a tangent line that is a tangent line of the bottom portion at the second point and extends along the plane is defined as a second tangent line,
when an intersection between the first tangent line and the second tangent line when viewed from the radial direction is defined as a third point, when viewed from the radial direction, the third point exists on a side opposite to the end portion on the trailing edge side of the blade-shaped portion across a straight line connecting the first point and the second point.