Gas turbine engine ceramic component assembly and bonding material

Patent metadata

Field	Value
Publication number	US-10648668-B2
Application number	US-201414904608-A
Country	US
Kind code	B2
Filing date	Jun 18, 2014
Priority date	Jul 19, 2013
Publication date	May 12, 2020
Grant date	May 12, 2020

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.

First claim

What is claimed is:

1. 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.

2. The gas turbine engine component assembly according to claim 1 , comprising a structure and a fastening assembly securing the metallic component to the structure.

3. The gas turbine engine component assembly according to claim 2 , wherein the metallic component is a portion of the fastening assembly.

4. The gas turbine engine component assembly according to claim 2 , wherein the ceramic is a monolithic ceramic.

5. The gas turbine engine component assembly according to claim 1 , wherein the ceramic is a ceramic matrix composite.

6. The gas turbine engine component assembly according to claim 1 , wherein the metallic component is a nickel alloy.

7. The gas turbine engine component assembly according to claim 1 , wherein the first and second thermal characteristics are a coefficient of thermal expansion.

8. The gas turbine engine component assembly according to claim 1 , wherein the metallic component includes titanium, and the refractory elements arranged in order of decreasing coefficient of thermal expansion, the refractory element with a greatest coefficient of thermal expansion arranged adjacent to the metallic component, and the refractory element with the greatest coefficient of thermal expansion selected from a group consisting of the following elements, in descending order of coefficient of thermal expansion: vanadium, rhodium, niobium, carbon, praseodymium, iridium, ruthenium, rhenium, tantalum, boron, hafnium, zirconium, osmium, chromium, molybdenum, tungsten, and silicon.

9. The gas turbine engine component assembly according to claim 1 , wherein the metallic component includes nickel, and the refractory elements are arranged in order of decreasing coefficient of thermal expansion, the refractory element with a greatest coefficient of thermal expansion arranged adjacent to the metallic component, and the refractory element with the greatest coefficient of thermal expansion selected from a group consisting of the following elements, in descending order of the coefficient of thermal expansion: thulium, cobalt, samarium, erbium, palladium, iron, beryllium, holmium, thorium, promethium, yttrium, terbium, scandium, lutetium, dysprosium, neodymium, gadolinium, platinum, vanadium, rhodium, niobium, carbon, praseodymium, iridium, ruthenium, rhenium, tantalum, boron, hafnium, zirconium, osmium, chromium, molybdenum, tungsten, and silicon.

10. The gas turbine engine component assembly according to claim 1 , wherein the first and second thermal characteristics are a modulus of elasticity.

11. The gas turbine engine component assembly according to claim 1 , wherein the first and second thermal characteristics are a shear modulus.

12. The gas turbine engine component assembly according to claim 11 , 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.

13. The gas turbine engine component assembly according to claim 1 , wherein the bonding material includes multiple layers of refractory elements, the refractory elements arranged in order of thermal characteristic value.

14. The gas turbine engine component assembly according to claim 1 , the bonding material including a partial transient liquid phase bond.

15. 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.

16. The gas turbine engine component assembly according to claim 15 , wherein the metallic component is a bracket.

17. The gas turbine engine component assembly according to claim 15 , wherein the fastening assembly includes a threaded fastener.

18. The gas turbine engine component assembly according to claim 15 , wherein the fastening assembly includes a hook.

19. 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.

Assignees

• United Technologies Corp

Inventors

• Cook Iii Grant O
• Abbott Michael G
• Mccaffrey Michael G

Classifications

• F05D2230/236

  Diffusion bonding · CPC title

• C09J2400/123

  in the substrate · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F01D11/08

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title