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.

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: 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: 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: 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. 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 with the turbine section disposed axially between the compressor section and the open propulsor rotor. The inlet section includes a flowpath inlet. The exhaust section includes a flowpath exhaust. At least a portion of the exhaust section is disposed axially between the open propulsor rotor and the open guide vane structure. 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.

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 for an aircraft propulsion system includes an open propulsor rotor and a powertrain configured to receive power from a turbine and drive both the propulsor rotor and a compressor section at the same time in a first mode of operation. In a second mode of operation, a brake is applied that stops rotation of the propulsor rotor and the turbine power received by the powertrain drives only the compressor section. In the second mode, the propulsor rotor is stationary or otherwise undriven which effectively prevents rotation of the propulsor rotor. This reduces or eliminates safety risks to ground crews resulting from an open propulsor rotor actively rotating as the aircraft is on the ground.

Abstract: An assembly for an aircraft propulsion system includes an open propulsor rotor and a powertrain configured to receive power from a turbine and drive both the propulsor rotor and a compressor section at the same time in a first mode of operation. In a second mode of operation, a brake is applied that stops rotation of the propulsor rotor and the turbine power received by the powertrain drives only the compressor section. In the second mode, the propulsor rotor is stationary or otherwise undriven which effectively prevents rotation of the propulsor rotor. This reduces or eliminates safety risks to ground crews resulting from an open propulsor rotor actively rotating as the aircraft is on the ground.

Abstract: An inspection method is provided during which a distal end of an inspection probe is inserted into an interior of a powerplant. The inspection probe includes a body and a head pivotally connected to the body. The head includes an actuator, and the head is disposed at the distal end of the inspection probe. The powerplant includes a component within the interior of the powerplant. The head is arranged with the component. The arranging includes pivoting the head relative to the body and abutting the head against a surface of the component. Vibrations in the component are induced using the actuator. A vibratory response in the component excited by the vibrations is measured using a sensor to provide sensor data.

Abstract: A turbine engine is provided that includes a first rotating assembly, a bearing, a turbine engine core and a flowpath. The first rotating assembly includes a propulsor rotor, a power turbine rotor and a power turbine shaft coupled with and axially between the propulsor rotor and the power turbine rotor. The bearing rotatably supports the first rotating assembly at an intermediate location along the power turbine shaft. The turbine engine core includes a second rotating assembly and a combustor. The second rotating assembly includes a core compressor rotor and a core turbine rotor. The power turbine rotor is arranged axially between the propulsor rotor and the second rotating assembly. The flowpath extends sequentially across the core compressor rotor, the combustor, the core turbine rotor and the power turbine rotor from an inlet into the flowpath to an exhaust from the flowpath.

Abstract: A turbine engine is provided that includes a propulsor rotor and an engine core. The propulsor rotor is rotatable about a propulsor axis. The engine core is configured to power operation of the propulsor rotor. The engine core includes a core compressor section, a core combustor section, a core turbine section, a first rotating structure and a second rotating structure. The first rotating structure includes a first compressor rotor arranged within the core compressor section. The first rotating structure is rotatable about a first structure axis which is offset from the propulsor rotor axis. The second rotating structure includes a second compressor rotor arranged within the core compressor section. The second rotating structure is rotatable about a second structure axis which is offset from the propulsor rotor axis and the first structure axis.

Abstract: A propulsion system for an aircraft includes an open propulsor rotor and a turbine engine. The turbine engine includes a fan section, an engine core, a first geartrain, a core flowpath and a bypass flowpath. The fan section includes a fan rotor. The engine core includes a first rotating assembly, a low pressure compressor section, a high pressure compressor section, a combustor section, a high pressure turbine section and a low pressure turbine section. The first rotating assembly drives rotation of the open propulsor rotor and the fan rotor through the first geartrain. The core flowpath extends through the low pressure compressor section, the high pressure compressor section, the combustor section, the high pressure turbine section and the low pressure turbine section. The bypass flowpath extends outside of and along the engine core.

Abstract: A propulsion system for an aircraft includes an open propulsor rotor and a turbine engine. The turbine engine includes a fan section, an engine core, a first geartrain, a core flowpath and a bypass flowpath. The fan section includes a fan rotor. The engine core includes a first rotating assembly, a low pressure compressor section, a high pressure compressor section, a combustor section, a high pressure turbine section and a low pressure turbine section. The first rotating assembly drives rotation of the open propulsor rotor and the fan rotor through the first geartrain. The core flowpath extends through the low pressure compressor section, the high pressure compressor section, the combustor section, the high pressure turbine section and the low pressure turbine section. The bypass flowpath extends outside of and along the engine core.

Abstract: A gas turbine engine support system includes a support arc segment piece that defines radially inner and outer sides, axially forward and aft sides, and first and second circumferential mate face sides. The radially inner side has a radially open socket that is configured to engage a mating component and transmit loads from the mating component. The radially open socket is elongated in an axial direction with respect to the axially forward and aft sides The support arc segment piece has radial and axial reaction surfaces that are configured, respectively, to transmit radial and axial components of the loads from the mating component.

Abstract: An apparatus comprises a variable pitch blade configured to connect with an endwall of an open rotor engine. The variable pitch blade defines a chamber therein on a bottom edge thereof. A retractable edge member pivotally connects within the chamber to move between a first position wherein at least a portion of the retractable edge member is located within the chamber and a second position wherein a portion of the retractable edge member extends downward from the bottom edge of the variable pitch blade to block a gap between the bottom edge of the variable pitch blade and the endwall.

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: A turbine engine with an axis is provided. This turbine engine includes a fan section, a turbine engine core, a bypass flowpath, a recovery system and a core flowpath. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. The bypass flowpath is fluidly coupled with and downstream of the fan section. The recovery system includes an evaporator module and a condenser module. The condenser module is arranged radially outboard of and axially overlaps the bypass flowpath. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module.

Abstract: A turbine engine with an axis is provided. This turbine engine includes a fan section, a turbine engine core, a bypass flowpath, an engine housing, an evaporator, a condenser and a core flowpath. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. The bypass flowpath is fluidly coupled with and downstream of the fan section. The engine housing includes a cavity radially outboard of and axially overlapping the fan section and/or the bypass flowpath. The evaporator module is within the cavity. The condenser module is within the cavity. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module.

Abstract: A propulsor includes a propulsor body and a prop assembly in rotational communication with the propulsor body. The prop assembly includes a plurality of prop blades configured for rotation about an axial centerline of the propulsor. The plurality of prop blades are rotatable between a deployed position and a stowed position. The propulsor further includes at least one linkage having a first linkage end and a second linkage end. The first linkage end of the at least one linkage is rotatably mounted to the propulsor body and the second linkage end is configured to be rotatably mounted to an aircraft body. The propulsor further includes a first motor coupled to the at least one linkage and configured to rotate the at least one linkage relative to the propulsor body between a first rotational position and a second rotational position.