Turbomachine blade
AssigneeALSTOM Technology Ltd
InventorsRalf Greim, Said Havakechian, Ivan William McBean
Life of this patent
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Abstract
The blades of a turbomachine comprise airfoils, which are bent such that the lean angle (φ), defined as the angle which the stacking line of the airfoil includes with the radial direction, and measured in the direction of rotation (ω), is variable along the width of the flow channel and decreases from the hub towards the housing.
Claims27
A turbomachine stator blade, comprising a blade airfoil, which extends with a longitudinal extent of the blade airfoil from a blade root to a blade tip, wherein the turbomachine stator blade has an installed radial direction, an installed circumferential direction and also an installed axial direction, and also a stacking line, wherein an angle of inclination is defined as the angle which a projection of the stacking line has with the installed radial direction, in a plane which is spanned by the installed circumferential direction and the installed radial direction, and wherein the angle of inclination (φ) varies along the longitudinal extent of the blade airfoil,
- wherein in the region of the blade tip the pressure face of the blade airfoil is oriented inwards in the installed radial direction, and the stacking line is convexly curved towards the pressure face of the blade airfoil, and
- wherein the blade airfoil extends at least radially in the root region, or by the pressure face is oriented outwards in the installed radial direction.
A turbomachine rotor blade, comprising a blade airfoil, which extends with a longitudinal extent of the blade airfoil from a blade root to a blade tip, wherein the turbomachine rotor blade has an installed radial direction, an installed circumferential direction and also an installed axial direction, and also a stacking line, wherein an angle of inclination is defined as the angle which a projection of the stacking line has with the installed radial direction, in a plane which is spanned by the installed circumferential direction and the installed radial direction, and wherein the angle of inclination (φ) varies along the longitudinal extent of the blade airfoil,
- wherein in the region of the blade root the suction face of the blade airfoil is oriented inwards in the installed radial direction, and the stacking line is convexly curved towards the suction face of the blade airfoil, and
- wherein the blade airfoil extends at least radially in the tip region, or by the suction face is oriented outwards in the installed radial direction.
Dependencies are inferred from the claim text.