Compliant sleeve for ceramic turbine blades
AssigneeAlliedSignal Inc.
InventorsHongda Cai, Dave Narasimhan, Thomas E. Strangman, Michael L. Easley, Bjoern Schenk
Life of this patent
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Abstract
A compliant sleeve for attaching a ceramic member to a metal member is comprised of a superalloy substrate having a metal contacting side and a ceramic contacting side. The ceramic contacting side is plated with a layer of nickel followed by a layer of platinum. The substrate is then oxidized to form nickel oxide scale on the ceramic contacting side and a cobalt oxide scale on the metal contacting side. A lubricious coating of boron nitride is then applied over the metal contacting side, and a shear-stress limiting gold coating is applied over the ceramic contacting side.
Claims20
A composite sleeve for mounting a ceramic member to a metal member comprising:
- a substrate have a metal contacting side and a ceramic contacting side, said metal contacting side configured to slideably engage said metal member and said ceramic contacting side configured to slideably engage said ceramic member;
- a soft layer over said ceramic contacting side and formed of a material having a lower yield strength than said substrate;
- and
- a first lubricant over said metal contacting side.
A compliant sleeve for attaching a ceramic member to a metal member comprising:
- a substrate having a metal contacting side and a ceramic contacting side;
- a soft layer over said ceramic contacting side and formed of a material having a lower yield strength than said substrate;
- a first lubricant over said metal contacting side;
- and
- a second lubricant over said soft layer, said second lubricant selected from a group consisting of gold, silver, molten glasses, boron nitride and boron oxides.
An assembly for a gas turbine engine comprising:
- a plurality of ceramic airfoils each having an airfoil portion and a root portion;
- a metal disk having a plurality of slots for receiving said root portions;
- and
- a plurality of compliant sleeves each sleeve disposed between one of said root portions and one of said slots and comprising a superalloy substrate having a metal contacting side configured to slideably engage said slot and a ceramic contacting side configured to slideably engage said root portion;
- a soft layer over said ceramic contacting side and formed of a material having a lower yield strength than said substrate;
- and
- a first lubricant over said metal contacting side.
An assembly for a gas turbine engine comprising:
- a plurality of ceramic airfoils each having an airfoil portion and a root portion;
- a metal disk having a plurality of slots for receiving said root portions;
- a plurality of compliant sleeves each sleeve disposed between said root portion and said slot and comprising a superalloy substrate having a metal contacting side and a ceramic contacting side;
- a soft layer over said ceramic contacting side and formed of a material having a lower yield strength than said substrate;
- a first lubricant over said metal contacting side;
- and
- a second lubricant over said soft layer, said second lubricant selected from a group consisting of gold, silver, molten glasses, boron nitride and boron oxides.
Dependencies are inferred from the claim text.