US 12,078,079 B2
Method for modifying blades of fan, compressor, and turbine of axial flow type, and blades obtained by the modification
Yasuhiro Okamura, Tokyo (JP); Masaaki Hamabe, Tokyo (JP); Daisuke Nishii, Tokyo (JP); and Juo Furukawa, Tokyo (JP)
Assigned to IHI CORPORATION, Tokyo (JP)
Filed by IHI CORPORATION, Tokyo (JP)
Filed on Apr. 6, 2023, as Appl. No. 18/296,576.
Application 18/296,576 is a continuation of application No. PCT/JP2021/029885, filed on Aug. 16, 2021.
Claims priority of application No. 2020-200993 (JP), filed on Dec. 3, 2020.
Prior Publication US 2023/0243264 A1, Aug. 3, 2023
Int. Cl. F01D 5/14 (2006.01)
CPC F01D 5/145 (2013.01) [F05D 2240/304 (2013.01); F05D 2250/14 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A blade for a fan, a compressor, or a turbine of axial-flow type, the blade comprising:
a base blade part having a tip region including a blade-end-side tip region and a midspan-side tip region located closer to a blade center than the blade-end-side tip region, and a hub region including a blade-end-side hub region and a midspan-side hub region located closer to the blade center than the blade-end-side hub region;
a suction-side elevated portion provided on a suction surface near a trailing edge in at least one of the blade-end-side tip region and the blade-end-side hub region of the base blade part; and
a pressure-side elevated portion provided on a pressure surface near the trailing edge in at least one of the midspan-side tip region and the midspan-side hub region of the base blade part,
the base blade part having a base airfoil including a leading-edge curve, a trailing-edge curve that is an arc, and a concave pressure-side curve and a convex suction-side curve each extending between the leading-edge curve and the trailing-edge curve at each of spanwise positions,
wherein
the blade has
the base airfoil in a spanwise region where neither the suction-side elevated portion nor the pressure-side elevated portion is provided,
a modified suction-surface airfoil in a spanwise region where the suction-side elevated portion is provided, and
a modified pressure-surface airfoil in a spanwise region where the pressure-side elevated portion is provided,
the modified suction-surface airfoil includes the leading-edge curve, the pressure-side curve and the suction-side curve of the base airfoil in the spanwise region where the suction-side elevated portion is provided, and a modified suction-surface trailing-edge curve,
the modified pressure-surface airfoil includes the leading-edge curve, the pressure-side curve and the suction-side curve of the base airfoil in the spanwise region where the pressure-side elevated portion is provided, and a modified pressure-surface trailing-edge curve,
the modified suction-surface trailing-edge curve includes a portion of the trailing-edge curve of the base airfoil in the spanwise region where the suction-side elevated portion is provided, the portion being closer to the pressure-side curve than the trailing edge, and an elevated portion curve,
the modified pressure-surface trailing-edge curve includes a portion of the trailing-edge curve of the base airfoil in the spanwise region where the pressure-side elevated portion is provided, the portion being closer to the suction-side curve than the trailing edge, and an elevated portion curve, and
the elevated portion curves include a concave front-side curve and a convex rear-side curve.