Abstract: An assembly is provided for an aircraft. This assembly includes a propulsion system and a control system. The propulsion system includes an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor about an axis. The control system includes a first sensor, a second sensor and a controller in signal communication with the first sensor and the second sensor. The first sensor is configured to provide first sensor data indicative of a first environmental parameter. The second sensor is mounted to the propulsion system and is configured to provide second sensor data indicative of a second environmental parameter. The controller is configured to monitor and/or control operation of the propulsion system using the first sensor data. The controller is also configured to monitor the first sensor data using the second sensor data.

Abstract: A first core turbine rotor of a first propulsion system is disposed in a first core turbine section and is configured to rotate in a first rotational direction. A first power turbine rotor is disposed in a first power turbine section and is configured to rotate in the first rotational direction. The first power turbine rotor is operatively coupled to a first open propulsor rotor. A second core turbine rotor of a second propulsion system is disposed in a second core turbine section and is configured to rotate in the first rotational direction. A second power turbine rotor is disposed in a second power turbine section and is configured to rotate in a second rotational direction that is opposite the first rotational direction. The second power turbine rotor is operatively coupled to a second open propulsor rotor.

Abstract: A propulsion system includes an open propulsor rotor, an open guide vane structure, a turbine engine and a blade actuation system. The open propulsor rotor includes a plurality of open propulsor blades. The turbine engine includes a compressor section and a rotating structure. The rotating structure is operatively coupled to the open propulsor rotor. The rotating structure includes a compressor rotor in the compressor section. The blade actuation system is configured to adjust pitch of at least one of the open propulsor blades. A controller is configured to control operation of the blade actuation system during aircraft flight to tailor the pitch. The turbine engine is configured to drive rotation of the open propulsor rotor about the axis during a first mode of operation. The open propulsor rotor is configured to windmill about the axis to drive rotation of the rotating structure during a second mode of operation.

Abstract: An assembly is provided for an aircraft. This assembly includes a propulsion system and a control system. The propulsion system includes an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor about an axis. The control system includes a first sensor, a second sensor and a controller in signal communication with the first sensor and the second sensor. The first sensor is configured to provide first sensor data indicative of a first environmental parameter. The second sensor is mounted to the propulsion system and is configured to provide second sensor data indicative of a second environmental parameter. The controller is configured to monitor and/or control operation of the propulsion system using the first sensor data. The controller is also configured to monitor the first sensor data using the second sensor data.

Abstract: A swirl recovery vane with acoustic treatment including a leading edge and a trailing edge opposite chordwise from the leading edge; an attachment region opposite spanwise from a tip region; a span dimension extending between the attachment region and the tip region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the swirl recovery vane; an acoustic panel receiver formed within the swirl recovery vane extending at least one of spanwise through the swirl recovery vane between the attachment region and the tip region or chordwise between the leading edge and the trailing edge; and an acoustic panel inserted into the acoustic panel receiver.

Abstract: An aircraft powerplant assembly includes a cooling plate, a first control valve and a first electric machine. The cooling plate includes a fluid cooling circuit, a cooling circuit inlet and a cooling circuit outlet. The fluid cooling circuit is disposed in the cooling plate and extends from the cooling circuit inlet to the cooling circuit outlet. The fluid cooling circuit includes a first circuit passage fluidly coupled between the cooling circuit inlet and the cooling circuit outlet. The first control valve is fluidly coupled between the cooling circuit inlet and the first circuit passage. A first controller housing is removably attached to the cooling plate and overlaps the first circuit passage. First controller circuitry is disposed within an interior of the first controller housing. The first controller circuitry is in thermal communication with the cooling plate through a wall of the first controller housing.

Abstract: An aircraft powerplant assembly includes a cooling plate, a first electric machine controller and a second electric machine controller. The cooling plate includes a fluid cooling circuit, a cooling circuit inlet and a cooling circuit outlet. The fluid cooling circuit extends within the cooling plate from the cooling circuit inlet to the cooling circuit outlet. A first controller housing is removably attached to the cooling plate and overlaps the fluid cooling circuit. First controller circuitry is in thermal communication with the cooling plate through a wall of the first controller housing. A second controller housing is removably attached to the cooling plate and overlaps the fluid cooling circuit. Second controller circuitry is in thermal communication with the cooling plate through a wall of the second controller housing.

Abstract: An aircraft propulsion system includes a propulsion section and a turbine engine. The propulsion section includes an open propulsor rotor and an open guide vane structure disposed next to the open propulsor rotor. The turbine engine is configured to drive rotation of the open propulsor rotor. The turbine engine includes an engine core, an inlet section, an exhaust section and a flowpath. The engine core includes a compressor section, a combustor section and a turbine section. The inlet section includes a flowpath inlet. The exhaust section includes a flowpath exhaust and a mixer at the flowpath exhaust. The flowpath extends from the flowpath inlet, through the inlet section, the compressor section, the combustor section, the turbine section and the exhaust section, to the flowpath exhaust. The mixer is configured to mix combustion products exhausted from the flowpath through the flowpath exhaust with ambient air outside of the propulsion system.

Abstract: A fan exit guide vane with acoustic treatment including a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the fan exit guide vane; and an acoustic zone integrally formed within the fan exit guide vane.

Abstract: A fan exit guide vane with acoustic treatment including a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the fan exit guide vane; an acoustic panel receiver formed within the fan exit guide vane extending at least one of spanwise through the fan exit guide vane between the radially inner attachment region and the radially outer attachment region or chordwise between the leading edge and the trailing edge; and an acoustic panel inserted into the acoustic panel receiver.

Abstract: A swirl recovery vane with acoustic treatment including a leading edge and a trailing edge opposite chordwise from the leading edge; an attachment region opposite spanwise from a tip region; a span dimension extending between the attachment region and the tip region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the swirl recovery vane; an acoustic zone integrally formed within the swirl recovery vane.

Abstract: A swirl recovery vane with structurally capable acoustic treatment including a leading edge and a trailing edge opposite chordwise from the leading edge; an attachment region opposite spanwise from a tip region; a span dimension extending between the attachment region and the tip region; a chord dimension extending between the leading edge and trailing edge; a pressure side opposite a suction side of the swirl recovery vane; a structural feature formed within the swirl recovery vane extending at least one of spanwise through the swirl recovery vane between the attachment region and tip region and/or chordwise between the leading edge and the trailing edge; an acoustic receiver formed within the structural feature extending at least one of spanwise through the swirl recovery vane between the attachment region and the tip region or chordwise between the leading edge and the trailing edge; and an acoustic panel inserted into the acoustic receiver.

Abstract: An assembly for an aircraft includes a first propulsion system and a second propulsion system. A first open propulsor rotor is configured to rotate in a first rotational direction about a first axis. A first engine core includes a first rotating structure with a first turbine rotor. A first rotating structure is configured to rotate in the first rotational direction about the first axis and drive rotation of the first open propulsor rotor through a first geartrain. A second open propulsor rotor is configured to rotate in a second rotational direction about a second axis that is opposite the first rotational direction. A second engine core includes a second rotating structure with a second turbine rotor. A second rotating structure is configured to rotate in the first rotational direction about the second axis and drive rotation of the second open propulsor rotor through a second geartrain.

Abstract: A fan exit guide vane with acoustic treatment including a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the fan exit guide vane; a structural feature and an acoustic receiver formed within the fan exit guide vane extending at least one of spanwise through the fan exit guide vane between the radially inner attachment region and the radially outer attachment region and/or chordwise between the leading edge and the trailing edge; and an acoustic panel inserted into the acoustic receiver.

Abstract: A swirl recovery vane with acoustic treatment including a leading edge and a trailing edge opposite chordwise from the leading edge; an attachment region opposite spanwise from a tip region; a span dimension extending between the attachment region and the tip region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the swirl recovery vane; an acoustic panel receiver formed within the swirl recovery vane extending at least one of spanwise through the swirl recovery vane between the attachment region and the tip region or chordwise between the leading edge and the trailing edge; and an acoustic panel inserted into the acoustic panel receiver.

Abstract: An assembly for an aircraft includes a first propulsion system and a second propulsion system. A first open propulsor rotor is configured to rotate in a first rotational direction about a first axis. A first engine core includes a first rotating structure with a first turbine rotor. A first rotating structure is configured to rotate in the first rotational direction about the first axis and drive rotation of the first open propulsor rotor through a first geartrain. A second open propulsor rotor is configured to rotate in a second rotational direction about a second axis that is opposite the first rotational direction. A second engine core includes a second rotating structure with a second turbine rotor. A second rotating structure is configured to rotate in the first rotational direction about the second axis and drive rotation of the second open propulsor rotor through a second geartrain.

Abstract: A propulsion system for an aircraft includes a propulsor rotor, a powerplant, a nacelle and a lockout system. The powerplant is coupled to and configured to drive rotation of the propulsor rotor. An electrical system for the powerplant is configured to receive electrical power from an electrical power source. The nacelle includes an access structure configured to move between a first position and a second position. The access structure at least partially covers the electrical system when in the first position. The access structure is arranged in the first position for propulsion system operation. The access structure is operable to be arranged in the second position for propulsion system maintenance and/or propulsion system inspection. The lockout system is configured to automatically trigger an operation to cut off the electrical power to the electrical system from the electrical power source when the access structure moves away from the first position.

Abstract: A propulsion system for an aircraft includes a first open propulsor rotor, a second open propulsor rotor, a turbine engine, a first drivetrain and a second drivetrain. The first drivetrain operatively couples the turbine engine to the first open propulsor rotor. The turbine engine is configured to drive rotation of the first open propulsor rotor through the first drivetrain during a first mode and a second mode. The second drivetrain is configured to operatively couple the turbine engine to the second open propulsor rotor during the first mode and to operatively decouple the turbine engine from the second open propulsor rotor during the second mode. The second drivetrain is configured as or otherwise includes a tower shaft. The turbine engine is configured to drive rotation of the second open propulsor rotor through the tower shaft during the first mode.

Abstract: A propulsion system for an aircraft includes a first open propulsor rotor, a second open propulsor rotor, a turbine engine and a drive system. The second open propulsor rotor is next to and downstream of the first open propulsor rotor. The turbine engine includes a flowpath, a compressor section, a combustor section, a turbine section and a rotating assembly. The rotating assembly includes a turbine rotor in the turbine section. The rotating assembly is configured to drive rotation of the first open propulsor rotor during a first mode and a second mode. The drive system is discrete from the rotating assembly. The drive system is configured to drive rotation of the second open propulsor rotor during the first mode. The second open propulsor rotor is rotationally fixed during the second mode.

Abstract: An assembly is provided for an aircraft powerplant. This assembly includes a vane structure and a heat exchanger. The vane structure extends longitudinally to a leading edge of the vane structure. The vane structure includes a translating body, a stationary body and an inlet passage. The translating body is configured to translate longitudinally between a first position and a second position. The translating body is configured to form the leading edge of the vane structure and close an inlet into the inlet passage when in the first position. The translating body is configured to open the inlet into the inlet passage when in the second position. The heat exchanger is disposed within the stationary body. The inlet passage projects into the stationary body from the inlet into the inlet passage to the heat exchanger.