Gas turbine engine ceramic component assembly and bonding material
AssigneeUnited Technologies Corporation
InventorsGrant O. Cook, III, Michael G. Abbott, Michael G. McCaffrey
Life of this patent
Estimating the term…
Abstract
A gas turbine engine component assembly includes a ceramic component having a first thermal characteristic. A metallic component has a second thermal characteristic. A bonding material secures the ceramic component to the metallic component. The bonding material includes at least one of a transient liquid phase bond and a partial transient liquid phase bond. The bonding material is configured to withstand a shear stress parameter relating to a differential between the first and second thermal characteristics.
Claims19
A gas turbine engine component assembly comprising:
- a ceramic component having a first thermal characteristic;
- a metallic component having a second thermal characteristic;
- a bonding material securing the ceramic component to the metallic component, the bonding material including at least one of a transient liquid phase bond and a partial transient liquid phase bond, the bonding material configured to withstand a shear stress parameter relating to a differential between the first and second thermal characteristics, wherein the bonding material includes multiple refractory elements, the refractory elements are arranged in order of coefficient of thermal expansion, the refractory element with a greatest coefficient of thermal expansion arranged adjacent to the metallic component;
- and
- wherein the component assembly is one of a blade, vane, blade outer air seal, combustor liner, and exhaust liner.
A gas turbine engine component assembly comprising:
- a ceramic component having a first thermal characteristic;
- a metallic component having a second thermal characteristic;
- a bonding material securing the ceramic component to the metallic component, the bonding material including at least one of a transient liquid phase bond and a partial transient liquid phase bond, the bonding material configured to withstand a shear stress parameter relating to a differential between the first and second thermal characteristics, wherein the bonding material includes multiple refractory elements, the refractory elements are arranged in order of coefficient of thermal expansion, the refractory element with a greatest coefficient of thermal expansion arranged adjacent to the metallic component;
- and
- wherein the ceramic component is a panel;
- and comprising a structure and a fastening assembly securing the metallic component to the structure.
A gas turbine engine component assembly comprising:
- a ceramic component having a first thermal characteristic;
- a metallic component having a second thermal characteristic;
- a bonding material securing the ceramic component to the metallic component, the bonding material including at least one of a transient liquid phase bond and a partial transient liquid phase bond, the bonding material configured to withstand a shear stress parameter relating to a differential between the first and second thermal characteristics, wherein the first and second thermal characteristics are one of a coefficient of thermal expansion, a modulus of elasticity, and a shear modulus;
- wherein the bonding material includes multiple refractory elements arranged in order of increasing shear modulus, the refractory element with a greatest shear modulus arranged adjacent to the metallic component, and the refractory element with a greatest coefficient of thermal expansion selected from a group consisting of the following elements, in increasing order of shear modulus:
- europium, ytterbium, lanthanum, praseodymium, neodymium, promethium, molybdenum, samarium, gadolinium, terbium, dysprosium, yttrium, holmium, lutetium, gold, erbium, scandium, silver, and hafnium;
- and
- the component assembly is one of a blade, vane, blade outer air seal, combustor liner, and exhaust liner.
Dependencies are inferred from the claim text.