Fuel-cooled engine component(s)
AssigneeRaytheon Technologies Corporation
InventorsDustin W. Davis, Lance L. Smith, Won-Wook Kim
Life of this patent
Estimating the term…
Abstract
An assembly is provided for a turbine engine with a flowpath. This assembly includes a fuel source and an engine component. The engine component forms a peripheral boundary of the flowpath. The engine component includes a component internal passage. The engine component is configured to receive fuel from the fuel source. The engine component is 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. The assembly is configured to direct the at least partially cracked fuel into the flowpath for combustion.
Claims20
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, 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.
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, and the engine component configured to receive fuel from the fuel source and flow the fuel within the component internal passage for cooling the engine component;
- wherein the assembly is configured to direct the fuel used for cooling the engine component from the engine component into the flowpath for combustion, and the fuel directed into the flowpath comprises hydrogen gas.
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.
Dependencies are inferred from the claim text.