Airfoil having internal lattice network

1. An airfoil comprising:

an airfoil body defining a longitudinal axis, the airfoil body including a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining a cavity in the airfoil body;

a lattice network connecting the first side wall and the second side wall, the lattice network including at least one enlarged node spaced apart from the first side wall and the second side wall and ribs extending from the at least one enlarged node, each of the ribs connecting to one of the first side wall and the second side wall; and

and a free-floating damper member adjacent the lattice network, the lattice network including at least one bearing surface contacting the free-floating damper member.

2. The airfoil as recited in claim 1 , wherein each of the ribs defines a central axis that is inclined relative to the longitudinal axis.

3. The airfoil as recited in claim 1 , wherein the at least one enlarged node has a cross-section in a direction perpendicular to the longitudinal axis that is greater in area than a cross-section of each of the ribs in the same direction.

4. The airfoil as recited in claim 1 , wherein each of the ribs connects to one of the first side wall or the second side wall at an enlarged wall node.

5. The airfoil as recited in claim 1 , wherein the at least one enlarged node includes a plurality of enlarged nodes longitudinally spaced apart from each other.

6. The airfoil as recited in claim 5 , wherein a first one of the ribs extends from a first one of the plurality of nodes and a second one of the ribs extends from a second one of the plurality of nodes, and the first rib and the second rib connect to one of the first side wall or the second side wall at a common wall node.

7. The airfoil as recited in claim 6 , wherein the one of the first side wall or the second side wall that includes the common wall node includes at least one cross-rib extending from the common wall node along the one of the first side wall or the second side wall that includes the common wall node.

8. The airfoil as recited in claim 5 , wherein the plurality of nodes and the ribs define at least one rectilinear opening in the lattice network.

9. The airfoil as recited in claim 1 , wherein the at least one enlarged node includes a plurality of enlarged nodes laterally spaced apart from each other with regard to the longitudinal axis.

10. The airfoil as recited in claim 1 , wherein the damper member is longitudinally elongated.

11. The airfoil as recited in claim 10 , wherein the damper member is located adjacent the leading edge.

12. The airfoil as recited in claim 1 , wherein the free-floating damper member is longitudinally elongated and is located adjacent the at least one enlarged node.

13. The airfoil as recited in claim 12 , wherein the at least one enlarged node includes the bearing surface.

14. The airfoil as recited in claim 12 , wherein the free-floating damper member extends through the lattice network.

15. A turbine engine comprising:

a compressor section;

a combustor in fluid communication with the compressor section; and

a turbine section in fluid communication with the combustor, the turbine section being coupled to drive the compressor section and the fan, and

at least one of the fan, the compressor section and the turbine section including an airfoil having an airfoil body defining a longitudinal axis, the airfoil body including a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining a cavity in the airfoil body, a lattice network connecting the first side wall and the second side wall, the lattice network including at least one enlarged node spaced apart from the first side wall and the second side wall and ribs extending from the at least one enlarged node, each of the ribs connecting to one of the first side wall and the second side wall, and a free-floating damper member adjacent the lattice network, the lattice network including at least one bearing surface contacting the free-floating damper member.

16. The turbine engine as recited in claim 15 , wherein each of the ribs defines a central axis that is inclined relative to the longitudinal axis.

17. The turbine engine as recited in claim 15 , wherein each of the ribs connects to one of the first side wall or the second side wall at an enlarged wall node.

18. A method for processing an airfoil, the method comprising:

depositing multiple layers of a powdered metal onto one another;

joining the layers to one another with reference to data relating to a particular cross-section of a blade; and

producing the airfoil with an airfoil body defining a longitudinal axis, the airfoil body including a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining a cavity in the airfoil body, a lattice network connecting the first side and the second side, the lattice network including at least one enlarged node spaced apart from the first side wall and the second side wall and ribs extending from the at least one enlarged node, each of the ribs connecting to one of the first side wall and the second side wall, and a free-floating damper member adjacent the lattice network, the lattice network including at least one bearing surface contacting the free-floating damper member.