Multi-metered film cooled blade tip
First Claim
1. A turbomachinery blade, comprising:
- an airfoil section having proximal and distal end portions and defining an internal cavity and an outer aerodynamic surface having a distal edge circumscribing the distal end portion, the distal end portion further defining at least one each of a first and a second metering orifice, and at least one metering cavity, the internal cavity, the at least one first metering orifice, the at least one metering cavity, and the at least one second metering orifice sequentially defining a fluid passage from the internal cavity to the distal edge.
1 Assignment
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Accused Products
Abstract
A rotating blade for a gas turbine engine is provided which is configured to uniformly diffuse cooling air from an internal cavity about the tip of the rotating blade. The rotating blade includes a secondary cavity interposed between an internal cavity and the peripheral edge of the blade tip, wherein the secondary cavity steps down the cooling air pressure, decreasing the momentum of the cooling air exiting the rotating blade tip. The cooling air is diffused about the tip of the rotating blade into cooling slots aligned along the peripheral edge, such that a sub-boundary layer of cooling air is built-up adjacent to surface of the airfoil.
28 Citations
23 Claims
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1. A turbomachinery blade, comprising:
an airfoil section having proximal and distal end portions and defining an internal cavity and an outer aerodynamic surface having a distal edge circumscribing the distal end portion, the distal end portion further defining at least one each of a first and a second metering orifice, and at least one metering cavity, the internal cavity, the at least one first metering orifice, the at least one metering cavity, and the at least one second metering orifice sequentially defining a fluid passage from the internal cavity to the distal edge. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19)
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20. A gas turbine engine blade, comprising:
a proximal end portion, a distal end portion, and an airfoil section therebetween, the airfoil section having an outer aerodynamic surface and defining an internal cavity, the distal end portion including a distal end surface of the blade, the distal end surface being substantially disposed on a longitudinal cross-section to the airfoil section, a distal edge, the distal edge being a perimeter outline of the distal end surface, a means for metering cooling fluid to flow from the internal cavity to a plurality of diffusion cooling slots defined along the distal edge by a plurality of discrete adjoining portions of the distal end surface and the outer aerodynamic surface. - View Dependent Claims (21, 22)
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23. A method for cooling a turbomachine blade, comprising the steps of:
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supplying cooling fluid into an internal cavity defined by an exterior wall of the blade, the exterior wall having an outer aerodynamic surface and a distal end surface, the outer aerodynamic surface and a distal end surface intersecting to form a distal edge surrounding the distal end surface, metering the cooling fluid through a first metering orifice from the internal cavity into an metering cavity proximate the distal edge and defined by the exterior wall of the blade, metering the cooling fluid through a second metering orifice from the metering cavity into a cooling slot defined by and along a portion of the distal edge.
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Specification