Double wall turbine parts
AssigneeGeneral Electric Company
InventorsMelvin Robert Jackson, David William Skelly, Raymond Grant Rowe, Donald George LaChapelle, Paul Stuart Wilson
Life of this patent
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Abstract
A double wall hot gas path part for turbines, such as an airfoil, combustor, duct or shroud, comprises an outer skin and an inner support wall that are metallurgically bonded to one another. The double wall contains integral channels for passage of cooling air adjacent to the skin. The skin may be a metal alloy skin or a microlaminate structure, including microlaminate composite structures. Microlaminate composites typically have a lower density than that of the material used for the support wall, and a simplified internal geometry, which promote weight reductions in the parts and increases in engine operating efficiency.
Claims20
A hot gas path turbine part having an outer double wall, comprising:
- a partially hollow support wall that is attached to and extends longitudinally from a base and has a shaped outer surface, said support wall being formed from a first material and having at least one longitudinally extending recessed channel formed in the shaped outer surface;
- and
- a skin made from a second material which conforms to, covers and is metallurgically bonded to the shaped outer surface of the support wall and covers the at least one longitudinally extending recessed channel, wherein the combination of the skin and the support wall form a double wall structure and the covered, recessed channel forms at least one longitudinally extending integral internal channel located within the double wall, and
- wherein the second material comprises an I.sub.S /M or I.sub.S /I.sub.M composite in the form of a microlaminate having a plurality of alternating layers of I.sub.S and M or I.sub.M.
Dependencies are inferred from the claim text.