Advanced protective coatings for gr-based nuclear propulsion fuel elements

Patent metadata

Field	Value
Publication number	US-10068675-B1
Application number	US-201414518075-A
Country	US
Kind code	B1
Filing date	Oct 20, 2014
Priority date	Nov 1, 2013
Publication date	Sep 4, 2018
Grant date	Sep 4, 2018

Abstract

A protective coating for a graphite (Gr) containing fuel element used in a nuclear thermal propulsion system includes a first layer that is configured to resist hot hydrogen attacks. The first layer has a coefficient of thermal expansion that is higher than a coefficient of thermal expansion of the Gr containing substrate. The coating also includes a plurality of second layers located between the first layer and the substrate. The second layers are configured to mitigate the differences in coefficients of thermal expansion between the first layer and the substrate to minimize debonding and exposure of the substrate to hydrogen attack. Preferably, the protective coating can comprise an outermost first layer including zirconium carbide (ZrC), a second layer including niobium (Nb), a third layer including molybdenum (Mo), and a fourth layer including molybdenum carbide (Mo2C) located adjacent to the substrate.

First claim

We claim:

1. A nuclear thermal propulsion system fuel element comprising:
a graphite-based substrate having a nuclear fuel embedded therein; and
a protective coating disposed on the graphite-based substrate, the protective coating comprising:
at least one first layer, wherein the at least one first layer is configured to resist hot hydrogen attacks, wherein the at least one first layer has a coefficient of thermal expansion that is higher than a coefficient of thermal expansion of the graphite-based substrate;
at least one second layer, wherein the at least one second layer is located between the at least one first layer and the graphite-based substrate, wherein the at least one second layer is configured to mitigate mismatch between coefficients of thermal expansion of the at least one first layer and the substrate, whereby debonding of the protective coating from the substrate is minimized; and
at least one third layer, wherein the at least one third layer is located between the at least one second layer and the graphite-based substrate, wherein there is a direct chemical reaction of the at least one third layer and the graphite-based substrate.

2. The nuclear thermal propulsion system fuel element according to claim 1 wherein the at least one first layer is a carbide.

3. The nuclear thermal propulsion system fuel element according to claim 2 wherein the at least one first layer includes ZrC.

4. The nuclear thermal propulsion system fuel element according to claim 1 wherein the at least one second layer includes Nb.

5. The nuclear thermal propulsion system fuel element according to claim 1 wherein the at least one third layer includes Mo.

6. The nuclear thermal propulsion system fuel element according to claim 5 wherein the at least one third layer comprises 100% Mo.

7. The nuclear thermal propulsion system fuel element according to claim 5 , wherein the protective coating further comprises:
at least one fourth layer located between the at least one third layer and the at least one second layer, wherein the at least one fourth layer includes an Mo—Nb alloy.

Assignees

• Nasa
• The Us Administrator Of National Aeronautics And Space Administration

Inventors

• Raj Sai V
• Stewart Mark
• Nesbitt James A

Classifications

• C09D5/08

  Anti-corrosive paints · CPC title

• G21C3/20 Primary

  with coating on fuel or on inside of casing; with non-active interlayer between casing and active material {with multiple casings or multiple active layers} · CPC title

• C08K3/14

  Carbides · CPC title

• G21C3/626

  Coated fuel particles · CPC title

• G21D5/02

  Reactor and engine structurally combined, e.g. portable · CPC title