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US 8,894,376 B2Granted
Turbomachine blade with tip flare
AssigneeGeneral Electric Company
InventorsChristopher Michael Penny, Ross James Gustafson
Life of this patent
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Abstract
Certain embodiments of the present disclosure include a system having a turbomachine including a plurality of turbomachine blades coupled to a rotor, wherein each turbomachine blade has a blade base portion and a flared blade tip portion flared relative to the blade base portion. Additionally, a trailing edge of each turbomachine blade extends along a common plane.
Claims20
A system, comprising:
- a turbomachine, comprising:
- a plurality of turbomachine blades coupled to a rotor, wherein each turbomachine blade of the plurality of turbomachine blades comprises an unflared blade base portion extending a first axial length of the turbomachine blade and a flared blade tip portion flared relative to the unflared blade base portion and extending a second axial length of the turbomachine blade, wherein a trailing edge of each turbomachine blade of the plurality of turbomachine blades extends along a common plane, the trailing edge of each turbomachine blade of the plurality of turbomachine blades is nonlinear, and the flared blade tip portion is flared at least partially in an axially forward direction relative to a rotational axis of the turbomachine.
A system, comprising:
- a turbomachine airfoil comprising an unflared base portion extending a first axial length of the turbomachine airfoil and a flared tip portion that is flared relative to the unflared base portion and extends a second axial length of the turbomachine airfoil, wherein a trailing edge of the turbomachine airfoil extends entirely along a common plane, the trailing edge of the turbomachine airfoil is nonlinear, and the flared tip portion is flared at least partially in an axially forward direction relative to a turbomachine rotational axis.
A system, comprising:
- a turbine blade comprising an unflared blade base portion extending a first axial length of the turbine blade and a flared blade tip portion extending a second axial length of the turbine blade, wherein the flared blade tip portion extends from the unflared blade base portion and is flared relative to the unflared blade base portion, a trailing edge of the turbine blade extends entirely along a common plane, the trailing edge is nonlinear, and the flared blade tip portion is flared at least partially in an axially forward direction relative to a turbine rotational axis.
Dependencies are inferred from the claim text.