Pitch angles of an aircraft engine rotor assembly
A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.
1. A method of operating an aircraft engine coupled to a wing of an aircraft comprising:
setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch; and
receiving data indicative of an operating condition of the aircraft engine, of the aircraft, or both during operation of the aircraft engine, and wherein setting the pitch of the plurality of rotor blades comprises setting the pitch of the plurality of rotor blades in response to the received data indicative of the operating condition of the aircraft engine, of the aircraft, or both;
wherein setting the pitch of the plurality of rotor blades comprises modifying the pitch of the plurality of rotor blades to non-uniform pitch angles along the circumferential direction such that the plurality of rotor blades define the first pitch at the first position and the second pitch at the second position, and wherein modifying the pitch of the plurality of rotor blades comprises increasing a ratio of a first airflow over the top of the wing to a second airflow over the bottom of the wing.
2. The method of claim 1 , wherein the plurality of rotor blades extend at least partially over a top of the wing when in the first position, and wherein the plurality of rotor blades extend at least partially below a bottom of the wing when in the second position.
3. The method of claim 1 , wherein the top of the wing is a suction side of the wing, and wherein the bottom of the wing is a pressure side of the wing.
4. The method of claim 1 , wherein the operating condition is a high lift operating condition.
5. The method of claim 1 , wherein the operating condition is at least one of a takeoff operating condition, a climb operating condition, a descent operating condition, or a landing operating condition.
6. The method of claim 1 , wherein receiving data indicative of the operating condition of the aircraft engine comprises receiving data indicative of an altitude, a change in altitude, an attitude of the aircraft, an ambient pressure, or an airspeed.
7. The method of claim 1 , wherein the rotor assembly of the aircraft engine is an unducted rotor assembly.
8. The method of claim 7 , wherein the aircraft engine is configured as a single unducted rotor engine comprising a turbomachine driving the unducted rotor assembly.
9. The method of claim 1 , wherein setting the pitch of the plurality of rotor blades comprises setting the pitch of the plurality of rotor blades with a pitch change mechanism.
10. The method of claim 1 , wherein the operating condition is a first operating condition, and wherein the method further comprises:
receiving data indicative of a second operating condition of the aircraft engine, the aircraft, or both, wherein the operating condition is indicative of a low lift operating condition; and
setting the pitch of the plurality of rotor blades to uniform pitch angles along the circumferential direction in response to receiving data indicative of the second operating condition such that the plurality of rotor blades define substantially the same pitch angles when in the first position as when in the second position.
11. An aircraft engine defining a circumferential direction, the aircraft engine comprising:
a turbomachine;
a rotor assembly comprising a plurality of rotor blades driven by the rotor assembly;
a pitch change mechanism operable with the plurality of rotor blades for changing a pitch of the plurality of rotor blades; and
a controller operably connected to the pitch change mechanism and configured to set a pitch of the plurality of rotor blades through the pitch change mechanism at non-uniform pitch angles along the circumferential direction such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch;
wherein in setting the pitch of the plurality of rotor blades the controller is configured to modify the pitch of the plurality of rotor blades to non-uniform pitch angles along the circumferential direction such that the plurality of rotor blades define the first pitch at the first position and the second pitch at the second position, and wherein modifying the pitch of the plurality of rotor blades comprises increasing a ratio of a first airflow over the top of the wing to a second airflow over the bottom of the wing.
12. The aircraft engine of claim 11 , wherein the controller is further configured to receive data indicative of an operating condition of the aircraft engine, an aircraft incorporating the aircraft engine, or both.
13. The aircraft engine of claim 12 , wherein the operating condition is a high lift operating condition.
14. The aircraft engine of claim 12 , wherein the operating condition is at least one of a takeoff operating condition, a descent operating condition, or a landing operating condition.
15. The aircraft engine of claim 11 , wherein the rotor assembly of the aircraft engine is an unducted rotor assembly.
16. The aircraft engine of claim 11 , wherein the controller is further configured to receive data indicative of an operating condition of the aircraft engine, an aircraft incorporating the aircraft engine, or both during operation of the aircraft engine, and wherein in setting the pitch of the plurality of rotor blades the controller is configured to set the pitch of the plurality of rotor blades in response to the received data indicative of the operating condition of the aircraft engine, of the aircraft, or both.
17. A method of operating an aircraft engine coupled to a wing of an aircraft comprising:
setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch; and
wherein in setting the pitch of the plurality of rotor blades comprises modifying the pitch of the plurality of rotor blades to non-uniform pitch angles along the circumferential direction such that the plurality of rotor blades define the first pitch at the first position and the second pitch at the second position, and wherein modifying the pitch of the plurality of rotor blades comprises increasing a ratio of a first airflow over the top of the wing to a second airflow over the bottom of the wing;
receiving data indicative of an operating condition of the aircraft engine, the aircraft, or both, wherein the operating condition is indicative of a low lift operating condition; and
setting the pitch of the plurality of rotor blades to uniform pitch angles along the circumferential direction in response to receiving data indicative of a second operating condition such that the plurality of rotor blades define substantially the same pitch angles when in the first position as when in the second position.