Turbine blade impingement baffle
AssigneeGeneral Electric Company
InventorsRobert J. Corsmeier, Harvey M. MacLin
Life of this patent
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Abstract
An impingement-cooled gas turbine blade includes an impingement baffle which, during engine operation, is subject only to shear loading. A tubular baffle body is provided with a pair of mounting flanges which are bonded between a forward portion of the turbine blade and an aft portion of the turbine blade. The bond extends from the blade dovetail to the blade tip.
Claims14
An impingement-cooled turbine blade, comprising:
- a front blade portion;
- an aft blade portion;
- a tubular impingement baffle integrally-bonded to and separating said front and aft blade portions along an entire radial height of said blade, said baffle extending from a tip portion of said blade through a dovetail portion of said blade and wherein said baffle includes a substantially planar baffle support plate having a periphery;
- and
- a blade airfoil outer surface comprising a portion of an outer surface of said front blade portion, a portion of an outer surface of said aft blade portion and a portion of said periphery of the support plate.
An impingement baffle for use in a gas turbine engine blade, said baffle comprising a tubular body having a perforated airfoil-shaped front portion and a substantially planar support plate extending transversely to opposite sides of said front portion and integrally connected to an aft portion of each of said opposite sides of said front portion, wherein said substantially planar support plate forms a radially extending boundary of said tubular body, said substantially planar support plate comprising connecting means projecting transversely from said opposite sides of said front portion for connecting said baffle to said turbine engine blade.
An impingement-cooled turbine blade comprising a dovetail portion, a platform portion and an airfoil portion having an outer surface and an impingement baffle disposed within said turbine blade and bonded along each of said dovetail, platform and airfoil portions, wherein said baffle includes a substantially planar support plate having a periphery, said periphery extending radially from a tip portion of said blade through said dovetail portion, and wherein said outer surface of said airfoil portion comprises a portion of said periphery.
Dependencies are inferred from the claim text.