Aircraft propulsion system with variable speed rotating structure
A propulsion system includes a first propulsor rotor, a second propulsor rotor and a gas turbine engine core. The first propulsor rotor is configured to generate propulsive thrust. The second propulsor rotor is configured to generate propulsive lift. The gas turbine engine core includes a compressor section, a combustor section, a turbine section and a rotating structure. The rotating structure includes a turbine rotor within the turbine section. The gas turbine engine core is configured to rotate the rotating structure at a first rotational speed during a first mode to drive the first propulsor rotor to generate the propulsive thrust. The gas turbine engine core is configured to rotate the rotating structure at a second rotational speed during a second mode to drive the second propulsor rotor to generate the propulsive lift. The second rotational speed may be less than eighty percent of the first rotational speed.
1 . A propulsion system for an aircraft, comprising:
a powertrain;
a first propulsor rotor configured to generate propulsive thrust;
a second propulsor rotor configured to generate propulsive lift; and
a thrust control system comprising an engine controller and a gas turbine engine core, the gas turbine engine core comprising a compressor section, a combustor section, a turbine section and a rotating structure, the rotating structure comprising a turbine rotor within the turbine section, the engine controller including a processing device and a memory, and the engine controller configured to selectively control operation of the gas turbine engine core, such that the gas turbine engine core operates in a first mode of operation and a second mode of operation, and the engine controller selectively controls operation of the gas turbine engine core such that an engine pressure ratio of the propulsion system decreases from a first engine pressure ratio during the first mode of operation to a second engine pressure ratio during the second mode of operation, the second engine pressure ratio lower than the first engine pressure ratio, to reduce the propulsive thrust generated by the first propulsor rotor;
the powertrain configured to couple the rotating structure to the first propulsor rotor and to decouple the rotating structure from the second propulsor rotor during the first mode of operation;
the gas turbine engine core configured to rotate the rotating structure at a first rotational speed during the first mode of operation to drive the first propulsor rotor to generate the propulsive thrust; and
the gas turbine engine core configured to rotate the rotating structure at a second rotational speed during the second mode of operation to drive the second propulsor rotor to generate the propulsive lift, wherein the second rotational speed is less than eighty percent of the first rotational speed,
wherein
the first propulsor rotor comprises a plurality of first blades, each of the plurality of first blades having a blade profile configured to generate higher propulsive thrust at the first rotational speed than at the second rotational speed; and
the second propulsor rotor comprises a plurality of second blades, each of the plurality of second blades having a blade profile configured to generate high a maximum propulsive lift at the second rotational speed.
2 . The propulsion system of claim 1 , wherein the second rotational speed is between fifty-five percent and seventy-five percent of the first rotational speed.
3 . The propulsion system of claim 1 , wherein the first engine pressure ratio is greater than 1.2.
4 . The propulsion system of claim 1 , wherein the second engine pressure ratio is less than 1.1.
5 . The propulsion system of claim 1 , wherein
the first engine pressure ratio is between 1.25 and 3.0; and
the second engine pressure ratio is between 1.01 and 1.06.
6 . The propulsion system of claim 1 , wherein
the gas turbine engine core is further configured to rotate the first propulsor rotor during the second mode; and
the first propulsor rotor is configured to generate at least one and one-half times more thrust during the first mode than during the second mode.
7 . The propulsion system of claim 1 , wherein the powertrain comprises a transmission configured to couple the second propulsor rotor to the rotating structure during second mode.
8 . The propulsion system of claim 1 , wherein the powertrain comprises a geartrain coupling the rotating structure to the first propulsor rotor and the second propulsor rotor.
9 . The propulsion system of claim 1 , wherein
the first propulsor rotor is rotatable about a first axis; and
the second propulsor rotor is rotatable about a second axis that is angularly offset from the first axis.
10 . The propulsion system of claim 1 , wherein the first propulsor rotor comprises a ducted rotor.
11 . The propulsion system of claim 1 , wherein the second propulsor rotor comprises an open rotor.
12 . The propulsion system of claim 1 , wherein the second propulsor rotor is one of a plurality of second propulsor rotors rotatably driven by the rotating structure during the second mode.
13 . The propulsion system of claim 1 , wherein
the gas turbine engine core further includes a second rotating structure;
the second rotating structure includes a compressor rotor within the compressor section and a second turbine rotor within the turbine section.
14 . A propulsion system for an aircraft, comprising:
a first propulsor rotor configured to generate propulsive thrust;
a second propulsor rotor configured to generate propulsive lift; and
a thrust control system comprising an engine controller and a gas turbine engine core, the gas turbine engine core comprising a compressor section, a combustor section, a turbine section and a rotating structure, the rotating structure comprising a turbine rotor within the turbine section, the engine controller including a processing device and a memory, and the engine controller configured to selectively control operation of the gas turbine engine core, such that the gas turbine engine core operates in a first mode of operation and a second mode of operation, and such that an engine pressure ratio of the propulsion system decreases from a first engine pressure ratio during the first mode of operation to a second engine pressure ratio during the second mode of operation, the second engine pressure ratio lower than the first engine pressure ratio, to reduce the propulsive thrust generated by the first propulsor rotor;
the gas turbine engine core configured to rotate the rotating structure during the first mode of operation to drive the first propulsor rotor to generate the propulsive thrust, and
the gas turbine engine core configured to rotate the rotating structure during the second mode of operation to drive the second propulsor rotor to generate the propulsive lift, and
the gas turbine engine core configured to rotate the rotating structure such that the propulsive thrust generated by the first propulsor rotor during the first mode of operation is 1.5 to 5 times greater than the propulsive thrust generated by the first propulsor rotor during the second mode of operation.
15 . The propulsion system of claim 14 , wherein the first engine pressure ratio is between 1.25 and 3.0.
16 . The propulsion system of claim 14 , wherein the second engine pressure ratio is between 1.01 and 1.06.
17 . The propulsion system of claim 14 , wherein
the gas turbine engine core is configured to rotate the rotating structure at a first rotational speed during the first mode to drive the first propulsor rotor to generate the propulsive thrust; and
the gas turbine engine core is configured to rotate the rotating structure at a second rotational speed during the second mode to drive the second propulsor rotor to generate the propulsive lift, and the second rotational speed is less than eighty percent of the first rotational speed.
18 . The propulsion system of claim 17 , wherein the second rotational speed is between fifty-five percent and seventy-five percent of the first rotational speed.
19 . An aircraft system, comprising:
a first output configured to generate propulsive thrust;
a second output configured to generate propulsive lift; and
a thrust control system comprising an engine controller and a gas turbine engine core, the gas turbine engine core comprising a compressor section, a combustor section, a turbine section and a rotating structure, the rotating structure comprising a turbine rotor within the turbine section, the engine controller including a processing device and a memory, and the engine controller configured to selectively control operation of the gas turbine engine core, such that the gas turbine engine core comprises a first mode of operation and a second mode of operation;
the gas turbine engine core configured to rotate the rotating structure at a first rotational speed during the first mode of operation to rotatably drive the first output, and the aircraft system having a first engine pressure ratio between 1.25 and 3.0 during the first mode; and
the gas turbine engine core configured to rotate the rotating structure at a second rotational speed during the second mode of operation to rotatably drive the second output, the second rotational speed between fifty-five percent and seventy-five percent of the first rotational speed, and the aircraft system having a second engine pressure ratio between 1.01 and 1.06 during the second mode;
wherein the engine controller selectively controls operation of the gas turbine engine core such that an engine pressure ratio of the aircraft system decreases from the first engine pressure ratio during the first mode of operation to the second engine pressure ratio during the second mode of operation to reduce the propulsive thrust generated by the first output.