Catalyst-containing material

Patent metadata

Field	Value
Publication number	US-12370528-B2
Application number	US-201917775652-A
Country	US
Kind code	B2
Filing date	Nov 25, 2019
Priority date	Nov 25, 2019
Publication date	Jul 29, 2025
Grant date	Jul 29, 2025

Abstract

A catalyst-containing material includes a refractory matrix and particles of one or more catalytic metal elements or catalytic oxides. The particles are dispersed through, and embedded in, the refractory matrix.

First claim

What is claimed is:

1. A catalyst-containing material comprising:
a refractory matrix; and
particles of one or more catalytic metal elements, the particles being dispersed through, and embedded in, the refractory matrix, wherein the particles of one or more catalytic metal elements include Ir, the refractory matrix includes one or more oxides selected from CeO 2 , HfO 2 , and combinations thereof, and including, by weight, 30% to 40% of the particles of the one or more catalytic metal elements, and 70% to 60% of the refractory matrix.

2. The catalyst-containing material as recited in claim 1 , wherein the particles of one or more catalytic metal elements additionally include one or more metals selected from Pt, Pd, Rh, Os, Ru, Re, and combinations thereof.

3. The catalyst-containing material as recited in claim 1 , wherein the particles of one or more catalytic metal elements additionally include one or more catalytic oxides selected from as V 2 O 5 , MnO 2 , and combinations thereof.

4. The catalyst-containing material as recited in claim 1 , wherein the refractory matrix additionally includes one or more oxides selected from ZrO 2 , Y 2 O 3 , Ln 2 O 3 , where Ln is a lanthanide element, and combinations thereof.

5. The catalyst-containing material as recited in claim 1 , wherein the refractory matrix is a binary composition of CeO 2 or HfO 2 , and an oxide selected from ZrO 2 , Y 2 O 3 , and Ln 2 O 3 , where Ln is a lanthanide element.

6. The catalyst-containing material as recited in claim 1 , wherein the refractory matrix is a binary composition of CeO 2 and HfO 2 .

7. The catalyst-containing material as recited in claim 1 , consisting of: the particles of the Ir and the refractory matrix of one or more oxides selected from CeO 2 , HfO 2 , and combinations thereof.

8. A thruster including a combustion chamber, an injector for providing propellant into the combustion chamber, and the catalyst-containing material of claim 1 disposed in the combustion chamber for catalyzing reaction of the propellant.

9. A method of fabricating a catalyst-containing material, the method comprising:
providing a mixture of matrix particles and particles of one or more catalytic metal elements;
combining the mixture with at least a binder to produce one or more green state bodies;
thermally treating the one or more green state bodies, the thermal treatment causing a sintering of the matrix particles to produce a refractory matrix with the particles of the one or more catalytic metal elements or the catalytic oxides dispersed through, and embedded in, the refractory matrix, wherein the particles of one or more catalytic metal elements include Ir, the refractory matrix includes one or more oxides selected from CeO 2 , HfO 2 , and combinations thereof, and including, by weight, 30% to 40% of the particles of the one or more catalytic metal elements, and 70% to 60% of the refractory matrix.

10. The method as recited in claim 9 , further comprising granulating the one or more green state bodies.

11. The method as recited in claim 9 , wherein the particles of the one or more catalytic metal elements additionally include one or more metals selected from Pt, Pd, Rh, Os, Ru, Re, and combinations thereof.

12. The method as recited in claim 9 , wherein the matrix particles additionally include one or more oxides selected from ZrO 2 , Y2O 3 , Ln 2 O 3 where Ln is a lanthanide element, and combinations thereof.

13. A thruster comprising:
a combustion chamber;
an injector for providing propellant into the combustion chamber;
an exit for discharging decomposition products from the combustion chamber; and
a catalyst-containing material in the combustion chamber for catalyzing reaction of the propellant, the catalyst-containing material including
a refractory matrix; and
particles of one or more catalytic metal elements dispersed through, and embedded in, the refractory matrix, wherein the particles of one or more catalytic metal elements include Ir, the refractory matrix includes one or more oxides selected from CeO 2 , HfO 2 , and combinations thereof, and including, by weight, 30% to 40% of the particles of the one or more catalytic metal elements, and 70% to 60% of the refractory matrix.

14. The thruster as recited in claim 13 , wherein the particles of the one or more catalytic metal elements additionally include one or more metals selected from Pt, Pd, Rh, Os, Ru, Re, and combinations thereof, the refractory matrix additionally includes an oxide selected from ZrO 2 , Y2O 3 , Ln 2 O 3 where Ln is a lanthanide element, and combinations thereof.

Assignees

• Aerojet Rocketdyne Inc

Inventors

• Wucherer Edward
• Glassy Benjamin Andrew

Classifications

• B01J2523/827

  Iridium · CPC title

• B01J2523/72

  Manganese · CPC title

• B01J2523/55

  Vanadium · CPC title

• B01J2523/49

  Hafnium · CPC title

• B01J2523/3712

  Cerium · CPC title