US 2013/0259668 A1 · Transonic Blade

Abstract

The present invention provides a transonic blade that concurrently achieves reduction in shock loss at a design point and improvement in stall margin in blades operating in a flow field of transonic speed or higher in an axial-flow rotating machine. A cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a stagger line connecting a leading edge with a trailing edge of the blade. A stacking line is shifted toward an upstream side of working fluid. The stacking line connects together respective gravity center positions of blade cross-sectional surfaces at spanwise positions in a range from a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine to a tip cross-sectional surface lying at a position most remote from the hub cross-sectional surface in a spanwise direction.

Claims13

Dependent claims

A transonic blade used in a flow field through which an overall or partial flow passes at a transonic speed or higher,

wherein the transonic blade is formed such that:
a cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a line connecting a leading edge with a trailing edge of the blade;
a stacking line is shifted toward an upstream side of working fluid, the stacking line connecting together gravity center positions of blade cross-sectional surfaces at respective spanwise positions in a range from a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine to a tip cross-sectional surface lying at a position most remote from the hub cross-sectional surface in a spanwise direction;
and
a maximum thickness position of the cross-sectional surface of the blade at each of the spanwise positions are shifted toward a trailing edge side of the blade in a range from the hub cross-sectional surface to the tip cross-sectional surface.

2 more elements

A transonic blade used in a flow field through which an overall or partial flow passes at a transonic speed or higher,

wherein the transonic blade is formed such that:
a cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a line connecting a leading edge with a trailing edge of the blade;
a stacking line connecting together gravity center positions of the cross-sectional surfaces of the blade at respective spanwise positions has a constant axial position on a hub cross-sectional surface side of a certain spanwise position between a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine and a mean cross-sectional surface located at a center in a spanwise direction and is shifted toward the upstream side of working fluid from the certain spanwise position to the tip cross-sectional surface side;
and
a maximum thickness position of the cross-sectional surface of the blade at each of the spanwise positions is shifted toward a trailing edge side of the blade in a range from the hub cross-sectional surface to the tip cross-sectional surface.

2 more elements

Dependencies are inferred from the claim text.

Transonic Blade

Life of this patent

Transonic Blade

Life of this patent

Abstract

Claims13