Ihi Corporation

Juo Furukawa

Masaaki Hamabe

Daisuke Nishii

Yasuhiro Okamura

Takuya Mitsukawa

Provided is a blade capable of optimizing an outflow angle in substantially the entire hub region and tip region, particularly in a blade-end-side hub region and a blade-end-side tip region. The blade includes: a base blade part; 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 a midspan-side tip region and a midspan-side hub region of the base blade part. An airfoil at each spanwise position where the elevated portion is provided is such that a trailing-edge curve of a base airfoil is changed to a modified trailing-edge curve. The modified trailing-edge curve includes a portion of the trailing-edge curve of the base airfoil in the spanwise region where the elevated portion is provided, the portion being closer to the pressure side or the suction side than the trailing edge, and an elevated portion curve. The elevated portion curve includes a concave front-side curve and a convex rear-side curve.

Method for modifying blades of fan, compressor, and turbine of axial flow type, and blades obtained by the modification

Provided are a method for designing a vane, which can reduce peaks of secondary flow losses appearing locally in secondary flow regions and a vane obtained by the designing. The method for designing a vane includes: a step of determining a base vane formed by stacking profiles having airfoil shapes in a spanwise direction along a stacking line which is configured as a smooth curved line having no inflection point or a straight line; and a step of changing the stacking line of the base vane to a smooth wavy curved line which waves in an axial direction of a fan, a compressor or a turbine and has no elbows.

Method for designing vane of fan, compressor and turbine of axial flow type, and vane obtained by the designing

A rotor blade includes a blade portion that extends in a spanwise direction from a hub portion to a tip portion and has a pressure-side surface and a suction-side surface, a blade portion is formed by profiles with airfoil shapes stacked in the spanwise direction, and a stacking line connecting gravity centers of the profiles at each spanwise position is a straight line parallel to a radial direction at a part from the hub portion to an outer end of a secondary flow region in a vicinity of the hub portion, and is a curved line, along which a distance measured from the straight line parallel to the radial direction toward a side of the suction-side surface gradually increases toward the tip portion, at a part from the outer end of the secondary flow region to the tip portion.

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Tokyo, Japan

Juo Furukawa