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US 2017/0248025 A1Published application
Turbine airfoil having near-wall cooling insert
AssigneeSiemens Energy, Inc.
InventorsNicholas F. Martin, JR., David J. Wiebe
Life of this patent
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AssigneeSiemens Energy, Inc.
InventorsNicholas F. Martin, JR., David J. Wiebe
Estimating the term…
A turbine airfoil is provided with at least one insert positioned in a cavity in an airfoil interior. The insert extends along a span-wise extent of the turbine airfoil and includes first and second opposite faces. A first near-wall cooling channel is defined between the first face and a pressure sidewall of an airfoil outer wall. A second near-wall cooling channel is defined between the second face and a suction sidewall of the airfoil outer wall. The insert is configured to occupy an inactive volume in the airfoil interior so as to displace a coolant flow in the cavity toward the first and second near-wall cooling channels. A locating feature engages the insert with the outer wall for supporting the insert in position. The locating feature is configured to control flow of the coolant through the first or second near-wall cooling channel.
(canceled)
The turbine airfoil according to claim 12 wherein the locating feature is flexible, being configured to allow the insert and the outer wall to move separately from each other.
The turbine airfoil according to claim 12, wherein the locating feature is configured as a tongue-in-groove arrangement, wherein a protrusion is formed on an inner surface of the outer wall that engages in a groove formed on the first or second face of the insert.
The turbine airfoil according to claim 12, wherein the locating feature comprises a protruding rib formed on the first or second face of the insert that engages with an inner surface of the outer wall.
The turbine airfoil according to claim 12, wherein the locating feature extends continuously along a radial extent of the insert, so as to divide the first or second near-wall cooling channel into adjacent flow passes separated by the locating feature, each flow pass conducting coolant in a generally radial direction.
The turbine airfoil according to claim 12, wherein the locating feature comprises multiple discontinuous supports oriented at an angle with respect to the radial direction, defining a coolant flow path having a zigzagged profile along the radial direction in the first or second near-wall cooling channel.
The turbine airfoil according to claim 12, wherein the insert is made of a material having a different coefficient of thermal expansion than the outer wall of the turbine airfoil.
(canceled)
A turbine airfoil comprising:
-20 (canceled)
Dependencies are inferred from the claim text.