Internally damped airfoiled component and method
An airfoiled component comprises: a root section, an airfoil section, a damper pocket enclosed within a portion of the airfoil section, and a damper. The airfoil section includes a suction sidewall and a pressure sidewall each extending chordwise between a leading edge and a trailing edge, and extending spanwise between the root section and an airfoil tip. The damper includes a fixed end unified with a damper mounting surface, and a free end extending into the damper pocket from the damper mounting surface.
1. A method of making an airfoiled component for a turbine engine, the method comprising:
(a) providing a first plurality of metal powder particles;
(b) directing an energy beam selectively over the first plurality of metal powder particles to form a first molten powder pool;
(c) solidifying at least a portion of the first molten powder pool to form a component wall build layer on a first deposition surface;
(d) providing a second plurality of metal powder particles;
(e) directing an energy beam selectively over the second plurality of metal powder particles to form a second molten powder pool;
(f) solidifying at least a portion of the second molten powder pool to form a damper build layer on a second deposition surface;
iteratively performing steps (a)-(c) to form an airfoil section comprising a plurality of successive component wall build layers, each of the plurality of successive component wall build layers formed on a corresponding plurality of successive first deposition surfaces, wherein the airfoil section includes at least one component wall bounding a damper pocket, the damper pocket having a damper mounting surface;
forming a temporary damper connection between a free end of at least one damper and a damper pocket surface spaced apart from the damper mounting surface, wherein the temporary damper connection comprises honeycombs;
iteratively performing steps (d)-(f) to form the at least one damper unified with the damper mounting surface, the at least one damper comprising a plurality of successive damper build layers;
wherein each of the plurality of successive damper build layers is formed on a corresponding plurality of successive second deposition surfaces; and
breaking apart the temporary damper connection via the application of at least one of heating and vibrating.
2. The method of claim 1 , wherein a first iteration of step (a) and a first iteration of step (d) are both performed prior to a first iteration of any of steps (b), (c), (e) and (f).
3. The method of claim 2 , wherein a first iteration of steps (b), (c), (e) and (f) are each performed subsequent to either a second iteration of step (a) or a second iteration of step (d).
4. The method of claim 1 , wherein a first iteration of steps (a)-(c) and a second iteration of steps (a)-(c) are performed prior to a first iteration of steps (d)-(f).
5. The method of claim 1 , further comprising:
enclosing the at least one damper within the damper pocket.
6. The method of claim 5 , wherein the enclosing step comprises:
layerwise forming a tip portion of the airfoil section.
7. The method of claim 5 , wherein the enclosing step comprises:
metallurgically bonding a separately formed tip portion to the airfoil section.
8. The method of claim 1 , wherein the damper pocket is bounded by one or more of: a suction sidewall, a pressure sidewall, and an internal rib.
9. The method of claim 1 , wherein the damper pocket comprises at least a portion of an airfoil cooling passage.
10. The method of claim 1 , wherein the first metal powder comprises a first airfoil alloy composition, and the second metal powder comprises a first damper alloy composition.
11. The method of claim 10 , wherein the first airfoil alloy composition is substantially different from the first damper alloy composition.
12. The method of claim 1 , wherein steps (a)-(f) are performed using an additive manufacturing apparatus selected from a group consisting of: a direct laser sintering (DLS) apparatus, a direct laser melting (DLM) apparatus, a selective laser sintering (SLS) apparatus, a selective laser melting (SLM) apparatus, a laser engineering net shaping (LENS) apparatus, an electron beam melting (EBM) apparatus, and a direct metal deposition (DMD) apparatus.
13. The method of claim 1 , wherein breaking apart the temporary damper connection comprises operating the airfoiled component in a break-in mode to break apart the temporary damper connection.