US 11,939,881 B2
Gas turbine rotor blade and gas turbine
Ryo Murata, Tokyo (JP); Yuji Komagome, Tokyo (JP); Naoya Tatsumi, Tokyo (JP); Hiroki Kitada, Tokyo (JP); and Shunsuke Torii, Tokyo (JP)
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
Filed by MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
Filed on Mar. 23, 2023, as Appl. No. 18/125,306.
Claims priority of application No. 2022-070022 (JP), filed on Apr. 21, 2022.
Prior Publication US 2023/0392505 A1, Dec. 7, 2023
Int. Cl. F01D 5/18 (2006.01); F01D 5/14 (2006.01); F01D 21/04 (2006.01); F04D 29/32 (2006.01); F04D 29/38 (2006.01)
CPC F01D 5/18 (2013.01) [F01D 5/14 (2013.01); F01D 5/141 (2013.01); F01D 5/147 (2013.01); F01D 5/187 (2013.01); F01D 21/045 (2013.01); F04D 29/324 (2013.01); F04D 29/38 (2013.01); F04D 29/384 (2013.01); F05D 2220/32 (2013.01); F05D 2240/30 (2013.01); F05D 2260/20 (2013.01)] 8 Claims
OG exemplary drawing
 
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.