Abstract: An aircraft propulsion system is mounted to an aircraft airframe. An open propulsor rotor of the propulsion system is configured to rotate about a rotational axis in a rotational direction within a plane of rotation. The propulsor rotor includes a propulsor blade with a blade tip and a blade span. The propulsor blade is configured to rotate about the rotational axis through a blade reference position in a reference direction towards a reference point on a fuselage. The propulsor blade is oriented vertically at the blade reference position. The blade tip is vertically offset from the reference point by an offset distance when the propulsor blade is at the blade reference position. The offset distance is equal to or less than fifty percent of the blade span. The reference point is coincident with the plane of rotation at a vertical periphery of the fuselage.

Abstract: A gas turbine engine having an axial centerline is provided that includes compressor, combustor, and turbine sections, a tangential on board injector (TOBI) system, and an HPC leakage guide structure. The compressor section has a high pressure compressor (HPC) that includes an HPC aft hub. The TOBI system extends circumferentially around the engine axial centerline, and has a plurality of nozzles and an inner radial flange. The HPC leakage guide structure has forward and aft ends. The forward end is disposed and configured to receive a leakage flow from the HPC and the aft end is engaged with the TOBI inner radial flange. The HPC leakage guide structure and the HPC aft hub define an HPC aft hub cavity. The HPC aft hub cavity extends between the forward and aft ends and has a flow area that is non-decreasing in a direction from the forward end to the aft end.

Abstract: An assembly for an aircraft propulsion system includes a first open propulsor rotor, a turbine engine, a pylon structure, a support structure, a second open propulsor rotor and a drive system. The turbine engine includes a flowpath, a compressor section, a combustor section, a turbine section and a rotating structure. The rotating structure includes a turbine rotor in the turbine section. The rotating structure is configured to drive rotation of the first open propulsor rotor. The pylon structure is mounted to the turbine engine. The support structure is arranged with the pylon structure independent of the turbine engine. The second open propulsor rotor is rotationally supported by the support structure. The drive system is configured to drive rotation of the second open propulsor rotor.

Abstract: An aircraft propulsion system, a propulsor section and a core engine section configured to generate an exhaust gas flow that is expanded through a turbine to drive a shaft for driving the fan. A propulsor mount assembly is attached to the propulsor section and supports the propulsor section on an aircraft structure and isolates loads generated in the propulsor section from the core engine section.

Abstract: An aircraft propulsion system includes a gas turbine engine, a power transfer assembly, and a controller. The gas turbine engine includes a first spool and a second spool. The power transfer assembly includes a first motor-generator, a second motor-generator, and a motor control assembly. The first motor-generator is operably coupled with the first spool. The second motor-generator is operably coupled with the second spool. The motor control assembly is electrically connected to the first motor-generator and the second motor-generator. The motor control assembly is configured to control an operating voltage of the power transfer assembly. The controller is connected in signal communication with the motor control assembly. The is controller is configured to identify a target operating voltage of the power transfer assembly selected in response to an aircraft altitude input to the controller and control the motor control assembly to control the operating voltage at the target operating voltage.

Abstract: An aircraft propulsion system includes a gas turbine engine and a power transfer assembly. The gas turbine engine includes a high-pressure (HP) spool and a low-pressure (LP) spool. The power transfer assembly includes a first motor-generator, a second motor-generator, a motor control assembly, and a common assembly housing. The first motor-generator is operably coupled with the HP spool. The second motor-generator is operably coupled with the LP spool. The first motor-generator is electrically connected to the second motor-generator. The motor control assembly is electrically connected to the first motor-generator and the second motor-generator. The motor control assembly is configured to operate the first motor-generator to apply a first rotational force to the HP spool or to operate the second motor-generator to apply a second rotational force to the LP spool. The common assembly housing houses the first motor-generator and the second motor-generator.

Abstract: An aircraft assembly includes first and second propulsion systems. Each of the propulsion systems includes an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor. The turbine engine includes a compressor section, a combustor section, a turbine section, a first rotating structure, a second rotating structure and a flowpath. The first rotating structure includes a first bladed rotor. The second rotating structure includes a second bladed rotor and is operable to rotate independent of the first rotating structure. The open propulsor rotor of the first propulsion system is configured to rotate a first rotational direction. The open propulsor rotor of the second propulsion system is configured to rotate a second rotational direction that is opposite the first rotational direction.

Abstract: An aircraft assembly includes first and second propulsion systems. Each propulsion system includes an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor. The turbine engine includes a compressor section, a combustor section, a turbine section, a first rotating structure, a second rotating structure and a flowpath. The flowpath extends through the compressor section, the combustor section and the turbine section with the first bladed rotor disposed between the second bladed rotor and the combustor section along the flowpath. The open propulsor rotor of the first propulsion system is configured to rotate a first rotational direction. The open propulsor rotor of the second propulsion system is configured to rotate a second rotational direction that is opposite the first rotational direction.

Abstract: A method is provided for operating an aircraft propulsion system. During this method, rotation of a propulsor rotor of the propulsion system is driven about a rotational axis. The propulsor rotor includes a plurality of rotor blades. A first blade pitch schedule is applied to the propulsor rotor while the propulsor rotor is rotating about the rotational axis such that: (a) a pitch of each of the rotor blades has a maximum blade pitch value when located at a first circumferential position about the rotational axis; (b) the pitch of each of the rotor blades has a minimum blade pitch value when located at a second circumferential position about the rotational axis; and (c) a reference line extending between the first circumferential position and the second circumferential position is angularly offset from a pitch axis of the aircraft by a first offset angle between zero degrees and forty-five degrees.

Abstract: An assembly is provided for an aircraft. This assembly includes an open propulsor rotor, an engine core and a geartrain. The open propulsor rotor is configured to rotate about an axis. The engine core includes a flowpath, a compressor section, a combustor section, a turbine section and a rotating structure. The flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath. The rotating structure includes a compressor rotor in the compressor section and a turbine rotor in the turbine section. The rotating structure is configured to rotate about the axis and drive rotation of the open propulsor rotor. The geartrain is disposed axially between and operatively couples the rotating structure and the open propulsor rotor. The geartrain includes a star gear system and a planetary gear system.

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 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: 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 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.