Cooled fuel injector system for a gas turbine engine and method for operating the same

1. A cooled fuel injector system of a combustor section of a gas turbine engine, at least a part of the fuel injector system is exposed to core gas flow traveling through the engine, the cooled fuel injector system comprising:

a source of a first cooling fluid, wherein the first cooling fluid is at a temperature lower than a temperature of the core gas flow proximate the fuel injector system; and

a fuel injector system component that includes a vascular engineered structure lattice (VESL) structure disposed between walls of the fuel injector system component, wherein the VESL structure is in fluid communication with the source of the first cooling fluid,

wherein the VESL structure includes:

a plurality of nodes, each node of the plurality of nodes comprising a node structure defining a hollow enclosure; and

a plurality of branches, each branch of the plurality of branches defining a hollow passage extending through the branch,

wherein only a single branch of the plurality of branches extends between and connects adjacent nodes of the plurality of nodes,

wherein the hollow enclosures and hollow passages of the respective plurality of nodes and plurality of branches define a first cooling flowpath through the fuel injector system component, and

wherein a space between the walls of the fuel injector system component and exterior surfaces of the plurality of nodes and the plurality of branches defines a second cooling flowpath through the fuel injector system component separate from the first cooling flowpath.

2. The cooled injector system of claim 1 , wherein the first cooling fluid includes hydrocarbon fuel of the same type injected into a combustion chamber of the combustor section through the fuel injector system, and wherein the fuel injector system is configured to pass the hydrocarbon fuel first cooling fluid into the combustion chamber after the first cooling fluid has passed through the VESL structure.

3. The cooled injector system of claim 1 , wherein the first cooling fluid through the fuel injector system component.

4. The cooled injector system of claim 1 , wherein first cooling flowpath is configured to convey the first cooling fluid through the fuel injector system component.

5. The cooled injector system of claim 4 , wherein the system further includes a source of a second cooling fluid, wherein the second cooling fluid is at a temperature lower than the temperature of the core gas flow proximate the fuel injector system; and wherein the second cooling flowpath is configured to convey the second cooling fluid through the fuel injector system component.

6. The cooled injector system of claim 5 , wherein the second cooling fluid is a cooled compressor bleed air.

7. The cooled injector system of claim 1 , wherein the VESL structure is disposed in a portion of the fuel injector system component that is exposed to the core gas flow during operation of the gas turbine engine.

8. A combustor section of a gas turbine engine, wherein the engine has a core gas flow traveling axially through the engine, the combustor section comprising:

a forward fuel injector system; and

a downstream fuel injector system, including at least one component that includes a vascular engineered structure lattice (VESL) structure disposed between walls of the at least one component, wherein the VESL structure is in fluid communication with a source of a first cooling fluid;

wherein the source of the first cooling fluid selectively provides the first cooling fluid to the at least one component at a temperature lower than a temperature of the core gas flow proximate the at least one component of the downstream fuel injector system, wherein the VESL structure includes:

a plurality of nodes, each node of the plurality of nodes comprising a node structure defining a hollow enclosure; and

a plurality of branches, each branch of the plurality of branches defining a hollow passage,

wherein only a single branch of the plurality of branches extends between and connects adjacent nodes of the plurality of nodes,

wherein the hollow enclosures and hollow passages of the respective plurality of nodes and plurality of branches define a first cooling flowpath through the at least one component, and

wherein a space between the walls of the at least one component and exterior surfaces of the plurality of nodes and the plurality of branches defines a second cooling flowpath through the at least one component separate from the first cooling flowpath.

9. A gas turbine engine, wherein the engine has a core gas flow traveling axially through the engine, comprising:

a compressor;

a combustor section in communication with the compressor, the combustor section having a forward fuel injector system, a downstream fuel injector system, and a combustion chamber, wherein both the forward and downstream fuel injection systems are in communication with the combustion chamber, and wherein the downstream fuel injector system includes at least one component having a vascular engineered structure lattice (VESL) structure disposed between walls of the at least one component, wherein the VESL structure is in fluid communication with a source of a first cooling fluid, and wherein the source of the first cooling fluid selectively provides the first cooling fluid to the at least one component at a temperature lower than a temperature of the core gas flow proximate the at least one component of the downstream fuel injector system; and

a turbine section in communication with the combustor section,

wherein the VESL structure includes:

a plurality of nodes, each node of the plurality of nodes comprising a node structure defining a hollow enclosure; and

a plurality of branches, each branch of the plurality of branches defining a hollow passage,

wherein only a single branch of the plurality of branches extends between and connects adjacent nodes of the plurality of nodes,

wherein the hollow enclosures and hollow passages of the respective plurality of nodes and plurality of branches define a first cooling flowpath through the at least one component, and

wherein a space between the walls of the at least one component and exterior surfaces of the plurality of nodes and the plurality of branches defines a second cooling flowpath through the at least one component separate from the first cooling flowpath.

10. A method of cooling a combustor section of a gas turbine engine, wherein the engine has a core gas flow traveling axially through the engine, the method comprising the steps of:

providing a combustor section having a forward fuel injector system, a downstream fuel injector system, and a combustion chamber with which both the forward and downstream fuel injection systems are in communication;

providing at least one vascular engineered structure lattice (VESL) structure disposed between walls of at least one component in the downstream fuel injector system;

providing fluid communication between the at least one VESL structure and a source of a first cooling fluid, wherein the first cooling fluid is at a temperature lower than a temperature of the core gas flow proximate the at least one component of the downstream fuel injector system; selectively passing the first cooling fluid through the at least one VESL structure within the at least one component, wherein the at least one VESL structure includes:

a plurality of nodes, each node of the plurality of nodes comprising a node structure defining a hollow enclosure; and

a plurality of branches, each branch of the plurality of branches defining a hollow passage,

wherein only a single branch of the plurality of branches extends between and connects adjacent nodes of the plurality of nodes,

wherein the hollow enclosures and hollow passages of the respective plurality of nodes and plurality of branches define a first cooling flowpath through the at least one component, and

wherein a space between the walls of the at least one component and exterior surfaces of the plurality of nodes and the plurality of branches defines a second cooling flowpath through the at least one component separate from the first cooling flowpath.

11. The method of claim 10 , wherein the step of selectively passing the first cooling fluid includes passing the first cooling fluid through the first cooling flowpath.

12. The method of claim 11 , further comprising the step of providing a source of a second cooling fluid, wherein the second cooling fluid is at a temperature lower than the temperature of the core gas flow proximate the downstream fuel injector system; and further comprising the step of selectively passing the second cooling fluid through the second cooling flowpath.

13. The cooled injector system of claim 1 , wherein the source of the first cooling fluid includes an outlet of a heat exchanger, and wherein an inlet of the heat exchanger receives diffuser case air.

14. The combustor section of claim 8 , wherein the source of the first cooling fluid includes an outlet of a heat exchanger, and wherein an inlet of the heat exchanger receives diffuser case air.

15. The gas turbine engine of claim 9 , wherein the source of the first cooling fluid includes an outlet of a heat exchanger, and wherein an inlet of the heat exchanger receives diffuser case air.

16. The method of claim 10 , wherein the source of the first cooling fluid includes an outlet of a heat exchanger, and wherein an inlet of the heat exchanger receives diffuser case air.

17. The cooled injector system of claim 1 , wherein at least one of the plurality of nodes and the plurality of branches comprises at least one augmentation feature protruding from an interior surface of the at least one of the plurality of nodes and the plurality of branches.

18. The cooled injector system of claim 1 , wherein each node of the plurality of nodes is connected to at least three other nodes of the plurality of nodes.