Fuel-cooled engine component(s)

1. An assembly for a turbine engine with a flowpath, comprising:

a fuel source; and

an engine component forming a peripheral boundary of the flowpath, the engine component comprising a component internal passage, the engine component configured to receive fuel from the fuel source, the fuel flows from a downstream side towards an upstream side with respect to the flowpath, and the engine component configured to crack at least some of the fuel within the component internal passage thereby cooling the engine component and providing at least partially cracked fuel;

wherein the assembly is configured to direct the at least partially cracked fuel into the flowpath for combustion in a combustion chamber of the turbine engine, and the at least partially cracked fuel comprises H 2 gas; and

wherein the engine component comprises material that at least partially forms the component internal passage, and the material comprises at least one of nickel (Ni), iron (Fe) or ruthenium (Ru).

2. The assembly of claim 1 , wherein

the fuel comprises ammonia; and

the at least partially cracked fuel further comprises N 2 gas.

3. The assembly of claim 1 , wherein the material is a catalytic material at least partially lining the component internal passage, and the catalytic material is selected to facilitate the cracking of the at least some of the fuel within the component internal passage.

4. The assembly of claim 1 , wherein

the fuel directed into the component internal passage comprises liquid fuel;

the engine component is configured to vaporize the liquid fuel to provide vaporized fuel; and

the engine component is further configured to crack at least some of the vaporized fuel to provide the at least partially cracked fuel.

5. The assembly of claim 1 , wherein

the fuel directed into the component internal passage comprises vaporized fuel; and

the engine component is configured to crack at least some of the vaporized fuel to provide the at least partially cracked fuel.

6. The assembly of claim 1 , wherein the engine component comprises a vane.

7. The assembly of claim 1 , wherein the engine component comprises a flowpath wall.

8. The assembly of claim 1 , further comprising:

a combustor comprising the combustion chamber, wherein the combustion chamber forms part of the flowpath;

the assembly configured to direct the at least partially cracked fuel into the combustion chamber for combustion.

9. The assembly of claim 8 , wherein

the combustor comprises a fuel injector; and

the fuel injector is configured to direct the at least partially cracked fuel into the combustion chamber for combustion.

10. The assembly of claim 8 , wherein

the combustor comprises the engine component;

the engine component is configured as a combustor wall; and

the combustor wall comprises one or more fuel injection orifices configured to direct the at least partially cracked fuel into the combustion chamber for combustion.

11. The assembly of claim 8 , further comprising:

a turbine vane adjacent the combustor;

the turbine vane comprising a vane internal passage that fluidly couples the fuel source with the component internal passage; and

the engine component configured as an inner wall of the combustor.

12. The assembly of claim 1 , further comprising an airframe component comprising an airframe internal passage that is fluidly coupled with the fuel source and the component internal passage.

13. An assembly for a turbine engine with a flowpath, comprising:

a fuel source containing non-hydrocarbon fuel; and

an engine component forming a peripheral boundary of the flowpath, the engine component comprising a component internal passage, and the engine component configured to receive the non-hydrocarbon fuel from the fuel source and flow the non-hydrocarbon fuel from a downstream side towards an upstream side, with respect to the flowpath, within the component internal passage for cooling the engine component;

wherein the assembly is configured to direct the non-hydrocarbon fuel used for cooling the engine component from the engine component into the flowpath for combustion, and the non-hydrocarbon fuel directed into the flowpath comprises H 2 gas; and

wherein the component internal passage is at least partially formed by a catalytic material, and the catalytic material comprises at least one of nickel (Ni), iron (Fe) or ruthenium (Ru).

14. The assembly of claim 13 , wherein the engine component is configured to crack at least some of the non-hydrocarbon fuel within the component internal passage to provide at least partially cracked fuel, and the at least partially cracked fuel comprises the H 2 gas.

15. An assembly for a turbine engine, comprising:

a fuel source, a turbine vane and an annular combustor;

the turbine vane comprising a vane internal passage;

the annular combustor comprising a combustion chamber and a combustor inner wall, and the combustor inner wall comprising an inner wall internal passage;

the assembly configured to direct fuel from the fuel source sequentially through the vane internal passage and the inner wall internal passage to cool the turbine vane and the combustor inner wall; and

the assembly configured to direct the fuel used for cooling the turbine vane and the combustor inner wall into the combustion chamber for combustion, wherein the fuel directed into the combustion chamber comprises H 2 gas;

wherein at least one of the vane internal passage or the inner wall internal passage is at least partially formed by a catalytic material, and the catalytic material comprises at least one of nickel (Ni), iron (Fe) or ruthenium (Ru).

16. The assembly of claim 15 , wherein

the annular combustor further includes a combustor outer wall that circumscribes the combustor inner wall;

the combustor outer wall comprises an outer wall internal passage;

the assembly is configured to direct additional fuel from the fuel source through the outer wall internal passage to cool the combustor outer wall; and

the assembly is configured to direct the additional fuel used to cool the combustor outer wall into the combustion chamber for combustion.

17. The assembly of claim 15 , wherein

at least one component of the assembly is configured to crack at least some of the fuel flowing therethrough to provide at least partially cracked fuel, and the assembly is configured to direct the at least partially cracked fuel into the combustion chamber for combustion; and

the at least one component of the assembly is configured as the turbine vane or the combustor inner wall.

18. The assembly of claim 15 , wherein the fuel directed into the combustion chamber further comprises N 2 gas.