Turbine component cooling channel mesh with intersection chambers
AssigneesSiemens Energy, Inc., Mikro Systems, Inc.
InventorsChing-Pang Lee, John J. Marra
Life of this patent
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Abstract
A mesh (35) of cooling channels (35A, 35B) with an array of cooling channel intersections (42) in a wall (21, 22) of a turbine component. A mixing chamber (42A-C) at each intersection is wider (W1, W2)) than a width (W) of each of the cooling channels connected to the mixing chamber. The mixing chamber promotes swirl, and slows the coolant for more efficient and uniform cooling. A series of cooling meshes (M1, M2) may be separated by mixing manifolds (44), which may have film cooling holes (46) and/or coolant refresher holes (48).
Claims20
A turbine component comprising:
- a mesh of cooling channels comprising an array of cooling channel intersections in a wall of the turbine component;
- a mixing chamber at each of a plurality of the cooling channel intersections;
- wherein each mixing chamber comprises a width that is wider than a respective width of each cooling channel connected thereto.
A turbine component comprising:
- a first plurality of parallel cooling channels in a layer below a surface of a wall of the component;
- a second plurality of parallel cooling channels in said layer;
- wherein the first plurality of parallel cooling channels intersects the second plurality of parallel cooling channels at an angle to define an interconnected mesh of the cooling channels comprising an array of intersections of the cooling channels, each intersection comprising a mixing chamber;
- wherein each mixing chamber comprises either a cylindrical shape with an axis centered on the intersection and normal to said surface or a spherical shape centered on the intersection;
- wherein each mixing chamber has a diameter greater than a width of said each cooling channel of the intersection at a mid-depth of the respective cooling channel.
A turbine airfoil comprising:
- a first plurality of parallel cooling channels in a layer below a surface of an outer wall of the airfoil;
- a second plurality of parallel cooling channels in said layer;
- wherein the first plurality of parallel cooling channels intersects the second plurality of parallel cooling channels at an angle of 60 to 75 degrees in a first interconnected mesh of the cooling channels comprising an array of intersections of the cooling channels, each intersection comprising a mixing chamber that is wider than each cooling channel of the intersection at a mid-depth of said each cooling channel of the intersection;
- wherein the cooling channels of the mesh are straight between the mixing chambers of the mesh;
- a coolant inlet manifold along an inlet side of said first interconnected mesh;
- a coolant mixing manifold in the wall along an outlet side of said first interconnected mesh and along an inlet side of a second interconnected cooling channel mesh within the layer;
- and
- wherein the coolant mixing manifold comprises film cooling outlet holes or coolant refresher inlet holes.
Dependencies are inferred from the claim text.