US 11,867,090 B2
Stator vane and aircraft gas turbine engine
Shinya Kusuda, Tokyo (JP)
Assigned to IHI Corporation, Tokyo (JP)
Filed by IHI Corporation, Tokyo (JP)
Filed on Jun. 22, 2022, as Appl. No. 17/808,114.
Application 17/808,114 is a continuation of application No. PCT/JP2021/007122, filed on Feb. 25, 2021.
Claims priority of application No. 2020-065756 (JP), filed on Apr. 1, 2020.
Prior Publication US 2022/0316351 A1, Oct. 6, 2022
Int. Cl. F01D 9/04 (2006.01)
CPC F01D 9/041 (2013.01) [F05D 2220/323 (2013.01); F05D 2240/129 (2013.01); F05D 2260/96 (2013.01)] 7 Claims
OG exemplary drawing
 
1. An assembly comprising a plurality of stator vanes provided rearward of a plurality of rotor blades, a stator vane of the plurality of stator vanes comprising:
an airfoil body having an airfoil cross section, wherein
a maximum airfoil thickness position of the airfoil body in the airfoil cross section satisfies following conditions at least on a tip side of the airfoil body:
(a) on a plane expanded in a circumferential direction in which the plurality of stator vanes are arranged, the maximum airfoil thickness position is located in a region between a trailing edge of the airfoil body and an intersection of the airfoil body, wherein the intersection is between the airfoil body and a line which is parallel to an extension line of a camber line of a rotor blade of the plurality of rotor blades at a trailing edge of the rotor blade of the plurality of rotor blades, the extension line also passes through a leading edge of a circumferentially adjacent stator vane of the plurality of stator vanes, and
(b) the maximum airfoil thickness position is located in a region between a position of a chord ratio 0.2 and a chord ratio 0.8, and
the chord ratio is a value obtained by dividing a distance from the leading edge of the airfoil body to a position on a chord of the airfoil body by a full length of the airfoil body chord.