CERAMIC COVERED TURBINE COMPONENTS
A component for a gas turbine engine comprises an underlying substrate. A plurality of ceramic panels have intermediate thermal expansion joints bonded by a bond layer to the underlying substrate. The thermal expansion joints are formed of a material having a greater coefficient of expansion than a material forming the ceramic panels. The ceramic panels and the thermal expansion joints are positioned to define an outer surface for the component. A gas turbine engine and a component for a gas turbine engine are also disclosed.
1 . A component for a gas turbine engine comprising:
an underlying substrate;
a plurality of ceramic panels having intermediate thermal expansion joints bonded by a bond layer to said underlying substrate, with said thermal expansion joints formed of a material having a greater coefficient of expansion than a material forming said ceramic panels, and said ceramic panels and said thermal expansion joints positioned to define an outer surface for the component.
2 . The component for a gas turbine engine as set forth in claim 1 , wherein said joint is a refractory thermal expansion joint formed of a metallic-based material or a ceramic-based material.
3 . The component for a gas turbine engine as set forth in claim 2 , wherein said underlying substrate is a metallic substrate.
4 . The component for a gas turbine engine as set forth in claim 1 , wherein said component includes an airfoil and said ceramic panels are mounted on said airfoil.
5 . The component for a gas turbine engine as set forth in claim 1 , wherein a cross-section of said joints between adjacent panels is generally rectangular.
6 . The component for a gas turbine engine as set forth in claim 1 , wherein a cross-section of said joint between said panels tapers in a direction toward said bond layer such that said joint traps said panels.
7 . The component for a gas turbine engine as set forth in claim 1 , wherein a cross-section of said joint between said panels tapers in a direction away from said bond layer such that an outer surface of said thermal expansion joint is minimized compared to an inner size of said cross-section of said thermal expansion joint.
8 . The component for a gas turbine engine as set forth in claim 1 , wherein a cross-section of said joint between said components includes smaller end portions and an enlarged central portion.
9 . The component for a gas turbine engine as set forth in claim 1 , wherein said panels have hollow backs with legs which are bonded to said substrate.
10 . The component for a gas turbine engine as set forth in claim 1 , wherein said panels have a surface area of less than or equal to about 2.0 in 2 (12.9 cm 2 ).
11 . The component for a gas turbine engine as set forth in claim 1 , wherein said panels have the surface area of greater than or equal to about 0.025 in 2 (0.16 cm 2 ) and less than or equal to about 0.25 in 2 (1.6 cm 2 ).
12 . The component for a gas turbine engine as set forth in claim 1 , wherein said bond layer is a transient liquid phase or partial transient liquid phase bond.
13 . A component for a gas turbine engine comprising:
an underlying substrate;
a plurality of ceramic panels having intermediate thermal expansion joints bonded by a bond layer to said underlying substrate, with said thermal expansion joints formed of a material having a greater coefficient of expansion than a material forming said ceramic panels, and said ceramic panels and said thermal expansion joints positioned to define an outer surface for the component;
said joints being a refractory thermal expansion joint formed of a metallic-based material or a ceramic-based material, said underlying substrate being a metallic substrate, said bond layer being a transient liquid phase or partial transient liquid phase bond;
said component including an airfoil and said ceramic panels being mounted on said airfoil; and
said panels having a surface area of less than or equal to about 2.0 in 2 (12.9 cm 2 ).
14 . A gas turbine engine comprising:
a compressor, and a turbine section, with a component in said turbine section;
said component including an underlying substrate;
a plurality of ceramic panels having intermediate thermal expansion joints bonded to said underlying substrate by a bond layer, with said thermal expansion joints formed of a material having a greater coefficient of expansion than a material forming said ceramic panels, and said ceramic panels and said thermal expansion joints positioned to define an outer surface for the component.
15 . The gas turbine engine as set forth in claim 14 , wherein said joint is a refractory thermal expansion joint formed of a metallic-based material or a ceramic-based material.
16 . The gas turbine engine as set forth in claim 14 , wherein said underlying substrate is a metallic substrate.
17 . The gas turbine engine as set forth in claim 14 , wherein said component includes an airfoil and said ceramic panels are mounted on said airfoil.
18 . The gas turbine engine as set forth in claim 14 wherein said bond layer is a transient liquid phase or partial transient liquid phase bond.
19 . The gas turbine engine as set forth in claim 14 , wherein said panels have a surface area of less than or equal to about 2.0 in 2 (12.9 cm 2 ).
20 . The gas turbine engine as set forth in claim 19 , wherein said panels have the surface area of greater than or equal to about 0.025 in 2 (0.16 cm 2 ) and less than or equal to about 0.25 in 2 (1.6 cm 2 ).