Controlling excitation loads associated with open rotor aeronautical engines
An open rotor aeronautical engine may include a core engine, a plurality of unducted airfoils, and a pitch change assembly. The pitch change assembly may include an ensemble actuator assembly and a unitary actuator assembly. The ensemble actuator assembly may have one or more ensemble actuators and a unison ring that is movable by actuation of the one or more ensemble actuators to collectively change a pitch angle of the plurality of unducted airfoils. The unitary actuator assembly comprising a plurality of unitary actuators respectively coupled to a corresponding one of the plurality of unducted airfoils, the plurality of unitary actuators respectively movable to change the pitch angle of the corresponding one of the plurality of unducted airfoils.
1 . An open rotor aeronautical engine comprising:
a core engine;
a plurality of unducted airfoils; and
a pitch change assembly comprising:
an ensemble actuator assembly comprising one or more ensemble actuators and a unison ring, the unison ring movable by actuation of the one or more ensemble actuators to collectively change a pitch angle of respective ones of the plurality of unducted airfoils; and
a unitary actuator assembly comprising a plurality of unitary actuators respectively coupled to a corresponding one of the plurality of unducted airfoils, the plurality of unitary actuators respectively movable to change the pitch angle of the corresponding one of the plurality of unducted airfoils, wherein respective ones of the plurality of unitary actuators comprise:
a course actuator that provides course adjustments to the pitch angle of the corresponding one of the plurality of unducted airfoils; and
a fine actuator that provides fine adjustments to the pitch angle of the corresponding one of the plurality of unducted airfoils.
2 . The open rotor aeronautical engine of claim 1 , wherein the unison ring, collectively translates to respective ones of the plurality of unducted airfoils, a linear motion, or a rotary motion.
3 . The open rotor aeronautical engine of claim 1 , wherein the ensemble actuator assembly comprises three ensemble actuators.
4 . The open rotor aeronautical engine of claim 1 , wherein the pitch change assembly comprises a guide vane-pitch change assembly, and the plurality of unducted airfoils comprise guide vanes.
5 . The open rotor aeronautical engine of claim 1 , wherein the pitch change assembly comprises a fan blade-pitch change assembly, and the plurality of unducted airfoils comprise fan blades.
6 . The open rotor aeronautical engine of claim 5 , wherein the unison ring comprises:
an outward unison ring;
an inward unison ring; and
a fan bearing assembly disposed between the inward unison ring and the outward unison ring.
7 . The open rotor aeronautical engine of claim 6 , wherein the outward unison ring defines part of a rotor portion of an unducted fan assembly, and the inward unison ring defines part of a stator portion of the unducted fan assembly.
8 . The open rotor aeronautical engine of claim 1 , wherein the plurality of unitary actuators are respectively coupled to the unison ring.
9 . The open rotor aeronautical engine of claim 8 , wherein the unitary actuator assembly comprises a plurality of linkage arms, respective ones of the plurality of linkage arms are respectively disposed between one of: (i) the unison ring and a corresponding one of the plurality of unitary actuators, or (ii) the corresponding one of the plurality of unducted airfoils and the corresponding one of the plurality of unitary actuators.
10 . The open rotor aeronautical engine of claim 9 , wherein at least one of the plurality of linkage arms have a length that differs from at least another one of the plurality of linkage arms.
11 . The open rotor aeronautical engine of claim 1 , wherein the course actuator has a stroke length corresponding to from 10% to 100% of a range of motion about a pitch axis of the corresponding one of the plurality of unducted airfoils, and the fine actuator has a stroke length corresponding to from 1% to 40% of the range of motion of the pitch axis of the corresponding one of the plurality of unducted airfoils.
12 . The open rotor aeronautical engine of claim 1 , wherein the pitch change assembly comprises a plurality of subgroup actuator assemblies, respective ones of the plurality of subgroup actuator assemblies including a subgroup actuator configured to change a pitch angle of an airfoil subgroup, the airfoil subgroup comprising a portion of the plurality of unducted airfoils.
13 . The open rotor aeronautical engine of claim 1 , wherein the plurality of unducted airfoils comprise guide vanes and fan blades, the fan blades being located upstream from the guide vanes.
14 . A pitch change assembly for an aeronautical gas turbine engine having a plurality of airfoils, the pitch change assembly comprising:
an ensemble actuator assembly comprising one or more ensemble actuators and a unison ring, the unison ring movable by actuation of the one or more ensemble actuators to collectively change a pitch angle of respective ones of the plurality of airfoils; and
a unitary actuator assembly comprising a plurality of unitary actuators respectively coupled to a corresponding one of the plurality of airfoils, the plurality of unitary actuators respectively movable to change the pitch angle of the corresponding one of the plurality of airfoils,
wherein respective ones of the plurality of unitary actuators comprise:
a course actuator that provides course adjustments to the pitch angle of the corresponding one of the plurality of airfoils; and
a fine actuator that provides fine adjustments to the pitch angle of the corresponding one of the plurality of airfoils.
15 . The pitch change assembly of claim 14 , wherein the pitch change assembly comprises a guide vane-pitch change assembly and wherein the plurality of airfoils comprise guide vanes, or wherein the pitch change assembly comprises a fan blade-pitch change assembly, and wherein the plurality of airfoils comprise fan blades.
16 . The pitch change assembly of claim 14 , wherein the unison ring comprises:
an outward unison ring;
an inward unison ring; and
a bearing assembly disposed between the inward unison ring and the outward unison ring.
17 . The pitch change assembly of claim 14 , wherein the unison ring translates, collectively to respective ones of the plurality of airfoils, a linear motion or a rotary motion.
18 . The pitch change assembly of claim 14 , wherein the ensemble actuator assembly comprises three ensemble actuators.
19 . The pitch change assembly of claim 14 , wherein the aeronautical gas turbine engine comprises an open rotor aeronautical gas turbine engine.