Airfoil structure having a shape memory alloy actuator
A fan blade includes a blade body and a shape memory alloy actuator. The blade body has a pressure side disposed opposite a suction side. Each of the pressure side and the suction side extends radially from a root towards a tip and extends axially from a leading edge towards a trailing edge. The blade body defines a passageway that is disposed between the pressure side and the suction side. The shape memory alloy actuator is received within the passageway and is operatively connected to the blade body.
1. A fan blade for a gas turbine engine, comprising:
a blade body having:
a pressure side disposed opposite a suction side;
a blade root radially spaced from a blade a tip;
a leading edge axially spaced from a trailing edge;
a plurality of passageways that:
extend radially between the blade root and the blade tip;
are disposed between the leading edge and the trailing edge; and
a plurality of a shape memory alloy actuator (SMA) portions that:
have a cellular structure,
are received within and have a shape conforming to the respective plurality of passageways;
are bonded to, and operatively connected to, and in sliding contact with the blade body; and
are selectively electrically driven to apply a stiffening load by an electrical actuator that is operatively connected to a power system in response to an operational parameter exceeding a threshold.
2. The fan blade of claim 1 , wherein the operational parameter is at least one of a vibration imposed on the blade body.
3. A fan blade for a gas turbine engine, comprising:
a blade body that extends radially from a root towards a tip and extends axially from a leading edge towards a trailing edge, the blade body structure having a plurality of of passageways with a respective plurality of shape memory alloy actuator (SMA) portions that are disposed therein, between the leading edge and the trailing edge, and extending radially from the root to the tip, the SMA portions being bonded to the blade body and being selectively electrically driven to apply a stiffening load by an electrical actuator that is operatively connected to a power system in response to an operational parameter exceeding a threshold.
4. The fan blade of claim 3 , wherein the SMA portions is made using an additive manufacturing process.
5. A gas turbine engine, comprising:
a fan section;
a compressor section disposed adjacent to the fan section;
a combustor section disposed adjacent to the compressor section;
a turbine section disposed adjacent to the combustor section; and
a fan blade incorporated into a rotor provided with at least one of the fan section and the compressor section, the fan blade comprising:
a blade body having:
a pressure side disposed opposite a suction side;
a blade root radially spaced from a blade tip;
a leading edge axially spaced from a trailing edge,
a plurality of passageways that:
extend radially between the blade root and the blade tip;
are disposed between the leading edge and the trailing edge; and
a plurality of a shape memory alloy actuator (SMA) portions that:
have a cellular structure;
are received within and have a shape conforming to the respective plurality of passageways;
are bonded to, and operatively connected to, and in sliding contact with, the blade body, and
are selectively electrically driven to apply a stiffening load by and electrical actuator that is operatively connected to a power system in response to an operational parameter exceeding a threshold; and
a sensor assembly in communication with the SMA portions, the sensor assembly arranged to provide a signal indicative of vibration of the fan blade to the power system; and
wherein the power system is configured to determine whether the operational parameter exceeds the threshold based on the signal.
6. The gas turbine engine of claim 5 , wherein the SMA portions are spaced apart from the tip of the blade body.
7. The gas turbine engine of claim 5 , wherein the sensor assembly includes a vibratory sensor that is disposed proximate the fan blade.
8. The gas turbine engine of claim 5 , wherein the SMA portions are embedded into the blade body.
9. The gas turbine engine of claim 8 , wherein the SMA portions are embedded into the blade body by an additive manufacturing process.
10. The gas turbine engine of claim 5 , wherein the SMA portions each have a first end that is operatively connected to an internal surface of the blade body proximate the tip and a second end that is operatively connected to the internal surface proximate the root.
11. The gas turbine engine of claim 10 , wherein the SMA portions are each defined by a first portion of a cellular structure.
12. The gas turbine engine of claim 11 , wherein the cellular structure is made using an additive manufacturing process.
13. The gas turbine engine of claim 12 , wherein the cellular structure is formed by a plurality of radially oriented lattice elements and axially oriented lattice elements, each of the lattice elements having a gradually variable thickness.
14. The gas turbine engine of claim 12 , wherein the cellular structure is formed by a transversely oriented lattice elements and angular lattice elements, each of the lattice elements having a gradually variable thickness.