Turbine blade and method
AssigneePratt & Whitney Canada Corp.
InventorChao Zhang
Life of this patent
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Abstract
The turbine blade includes an airfoil, a root connected to the airfoil and having lobed edges spaced apart on laterally opposed sides of an axis extending axially through the root, and an air passage extending through the airfoil and the root. A first tab extends at least partially along and laterally outward from a first edge of the laterally opposed lobed edges, and a second tab extending at least partially along and laterally outward from a second edge of the laterally opposed lobed edges.
Claims17
A turbine blade adapted to be mounted to a disc, the disc having a lobed slot therein for receiving the turbine blade, the turbine blade comprising:
- an airfoil;
- a root connected to the airfoil and adapted to be received with the lobed slot of the disc, the root defining an axis that extends axially therethrough, the root defining lobes having lateral surfaces extending axially between an upstream-facing surface and a down-stream facing surface of the root, the lateral surfaces of the lobes having lobed edges formed at junctions between the upstream-facing surface and the lateral surfaces of the root;
- an air passage extending through the airfoil and the root;
- a first tab connected to the upstream-facing surface of the root, the first tab being upstream of and axially spaced apart from the lateral surfaces of the lobes, an outer portion of the first tab extending laterally outward from a first edge of the lobed edges to overlap an upstream surface of the disc, at least the outer portion of the first tab having a shape conforming to that of the first edge;
- and
- a second tab connected to the upstream-facing surface of the root, the second tab being upstream of and axially spaced apart from the lateral surfaces of the lobes, an outer portion of the second tab extending laterally outward from a second edge of the lobed edges in a direction opposite the first tab such as to overlap an upstream surface of the disc, at least the outer portion of the second tab having a shape conforming to that of the second edge.
A turbine rotor for a gas turbine engine, comprising:
- a disc rotatable about a rotation axis and having a circumferential array of slots therein, slots extending generally axially in the disc relative to the rotation axis;
- a plurality of turbine blades received in the slots, the blades having fir-tree-shaped roots configured with the slot to form a mating connection between the disc and the turbine blades;
- the turbine blades having one or more tabs located on an upstream-facing surface of the fir-tree-shaped roots, the one or more tabs extending laterally outward from a lateral outer edge of the fir-tree-shaped roots on circumferentially opposite sides of the fir-tree-shaped roots, the one or more tabs extending laterally in an circumferential direction over an upstream surface of the disc thereby sealing a lateral portion of a gap defined between the fir-tree-shaped roots and the disc, the one or more tabs having a shape conforming to the lateral outer edge of the fir-tree-shaped roots, a radially inner end of the upstream surface of the fir-tree-shaped roots being free of the one or more tabs;
- and
- a cover plate connected to an upstream-facing side of the disc and defining a first air passage between the cover plate and the disc, and wherein the disc and the given turbine blade define a second air passage fluidly connected to the first air passage extending through the root of the given turbine blade to an airfoil portion of the given turbine blade.
Dependencies are inferred from the claim text.