Abstract: An assembly for an aircraft propulsion system includes a housing structure, a guide vane structure, and a front mount assembly. The housing structure includes an engine case assembly. The engine case assembly includes a front center body. The guide vane structure includes a guide vane structure base. The front mount assembly is mounted on the front center body. The front mount assembly is disposed axially coincident with the guide vane structure. The front mount assembly includes at least one pylon attachment linkage.

Abstract: An assembly for an aircraft propulsion system includes an open propulsor rotor, a housing structure, and a turbine engine core. The open propulsor rotor includes a plurality of open propulsor blades arranged circumferentially around an axis. Each of the plurality of open propulsor blades projects radially out into an environment external to the aircraft propulsion system. The housing structure includes an engine case assembly and a nacelle. The nacelle forms at least a portion of an exterior flow boundary for the aircraft propulsion system. The nacelle forms a guide vane structure receptacle at the exterior flow boundary. The nacelle further includes a nacelle interior skeletal structure disposed at the guide vane structure receptacle. The turbine engine core is housed within the engine case assembly. The turbine engine core is configured to drive rotation of the open propulsor rotor about the axis.

Abstract: An assembly for an aircraft propulsion system includes a housing structure. The housing structure includes an engine case assembly and a nacelle. The nacelle is disposed radially outboard of the engine case assembly. The nacelle forms at least a portion of an exterior flow boundary for the aircraft propulsion system that borders an environment external to the aircraft propulsion system. The nacelle includes a nacelle interior skeletal structure mounted to the engine case assembly at a forward mount and an aft mount.

Abstract: An assembly for an aircraft propulsion system includes a housing structure, an open guide vane structure, and a flowpath. The housing structure includes an upstream housing end and a pylon structure. The pylon structure includes a main pylon body and a front center body attached to the main pylon body. The front center body is disposed at the upstream housing end. The front center body includes an outer radial case structure and an inner radial case structure extending circumferentially about an axis of the aircraft propulsion system. The open guide vane structure includes a guide vane structure base disposed at the outer radial case structure. The flowpath extends through the aircraft propulsion system from an inlet into the flowpath to an exhaust from the flowpath. The inlet is formed by the front center body between the outer radial case structure and the inner radial case structure.

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 vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section. A spar has a spar platform adjacent the first fairing platform and a spar leg that extends through the hollow airfoil section. The spar leg has an end portion protruding from the second fairing platform. The end portion has a clevis mount. A support platform adjacent the second fairing platform has a through-hole through which the end portion of the spar leg extends. A pin extends though the clevis mount and locks the support platform to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform. The clevis mount includes first and second prongs. The first prong has a pin hole, and the pin is disposed through the pin hole and cantilevered with respect to the first prong.

Abstract: An assembly includes first vanes, second vanes, a rotor and an actuation system. The actuation system includes a first ring and a second ring. The first ring is coupled to each first vane. The second ring is coupled to each second vane. During a first mode, the actuation system is configured to rotate the first ring in a first rotational direction about the axis, rotate the second ring in a second rotational direction about the axis, and pivot each of the first vanes and each of the second vanes in a common first pivot direction. During a second mode, the actuation system is configured to rotate the first ring in the second rotational direction about the axis, rotate the second ring in the first rotational direction about the axis, and pivot each of the first vanes and each of the second vanes in a common second pivot direction.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a propulsion module, a gas generator and an anti-icing system. The propulsion module includes an open propulsor rotor. The gas generator is configured to drive rotation of the open propulsor rotor about an axis. The gas generator includes a flowpath, a compressor section, a combustor section, a turbine section and an exhaust section. The flowpath extends through the compressor section, the combustor section, the turbine section and the exhaust section. The turbine section is axially between the combustor section and the open propulsor rotor along the axis. The anti-icing system is configured to bleed gas from the flowpath in the exhaust section to provide heated gas. The anti-icing system is configured to direct the heated gas to the propulsion module to reduce or prevent ice accumulation on an exterior surface of the propulsion module.

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: 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: 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: 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 vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section. A spar has a spar platform adjacent the first fairing platform and a spar leg that extends through the hollow airfoil section. The spar leg has an end portion protruding from the second fairing platform. The end portion has a clevis mount. A support platform adjacent the second fairing platform has a through-hole through which the end portion of the spar leg extends. A pin extends though the clevis mount and locks the support platform to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform. The clevis mount includes first and second prongs. The first prong has a pin hole, and the pin is disposed through the pin hole and cantilevered with respect to the first prong.

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.