Method of forming a catalyst element having a thermal barrier coating as the catalyst substrate
View Patent ↗A combustion catalyst coating ( 36 ) applied to the surface of a ceramic thermal barrier coating ( 34 ) which is supported by a metal substrate ( 32 ). The microstructure of the thermal barrier coating surface provides the necessary turbulent flow and surface area for interaction of the catalyst and a fuel-air mixture in a catalytic combustor of a gas turbine engine. The temperature gradient developed across the thermal barrier coating protects the underlying metal substrate from a high temperature combustion process occurring at the catalyst surface. The thermal barrier coating deposition process may be controlled to form a microstructure having at least one feature suitable to interdict a flow of fuel-air mixture and cause the flow to become more turbulent than if such feature did not exist.
1. A method of forming a catalyst element, the method comprising:
providing a substrate having a surface;
depositing a plasma sprayed ceramic thermal barrier coating material over the substrate having a specific surface area of less than about 18 m 2 /g effective to provide an increased amount of catalic reactions per surface area of the coating per unit flow on the catalic element; and
depositing a combustion catalyst material over the ceramic thermal barrier coating material.
2. The method of claim 1 , farther comprising depositing a ceramic wash-coat over ceramic Thermal barrier coating material prior to the step of depositing a combustion catalyst material.
3. The method of claim 1 , further comprising depositing the ceramic thermal barrier coating by a plasma spray process.
4. The method of claim 3 , further comprising controlling deposition parameters during the plasma spray deposition process to support the development of features suitable to interdict a flow of fuel-air mixture and cause the flow to become more turbulent than if such feature did not exist.
5. The method of claim 4 , wherein the step of controlling deposition parameters comprises controlling at least one of a feed rate, a particle size, a temperature, a rotation rate, and a spray angle.
6. The method of claim 1 , wherein the substrate is a formed as a sheet or a tube.
7. The method of claim 1 , wherein the substrate is formed substantially flat or corrugated.
8. A method of forming a catalyst element, the method comprising:
providing a metal substrate having a surface; and
depositing a plasma sprayed thermal barrier coating material over the metal substrate having a specific surface area of less than about 18 m 2 /g effective to function as a catalytic material at an exposed surface of the thermal barrier coating and provide an increased amount of catalytic reactions per surface area of the coating per unit flow on the catalytic element.
9. The method of claim 8 , further comprising depositing a combustion catalyst material over the thermal barrier coating material.
10. The method of claim 8 , wherein the catalytic material comprises one of the group of:
pyrochlores with the formula A 2 B 2 O 7 or AB 2 O 6 where A is selected from the rare earth elements and B is selected from the group of zirconium, hathium, titanium, niobium and tantalum;
perovskites with the formula ABO 3 where A is selected from the group of rare earth elements, alkaline earth elements and manganese, and B is selected from the group of aluminum, chrome, tungsten, zirconium, hafnium, titanium, niobium, tantalum, iron, manganese, cobalt, nickel and chrome;
garnets with the formula A 3 Al 5 O 12 where A is selected from the group of rare earth elements;
the hexaluminates LaAl 11 O 18 , BaMnAl 11 O 18 , BaAl 12 O 19 , and BaMAl 11 O 19 where M is selected from the group of chrome, manganese, iron, cobalt and nickel; and
spinels with the formula AB 2 O 4 where A is selected from the group of alkaline earth elements and B is selected from the group of aluminum, iron, manganese, cobalt, chrome and nickel.
11. The method of claim 8 , wherein the catalytic material comprises a pyrochlore with the formula A 2 B 2 O 7 or AB 2 O 6 where A is selected from the rare earth elements and B is selected from the group of zirconium, hafnium, titanium, niobium and tantalum.