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 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.

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: An assembly is provided for an aircraft powerplant. This assembly includes a bladed rotor, a shroud and an actuation system. The bladed rotor includes a rotor base and a plurality of rotor blades arranged circumferentially around and connected to the rotor base. The shroud is adjacent tips of the rotor blades. The actuation system includes a water source and an actuator coupled to the shroud. The actuation system is configured to direct a quantity of water from the water source to the actuator to control clearance between the shroud and the tips of the rotor blades.

Abstract: A turbine engine is provided that includes a bypass flowpath, a plurality of upstream vanes and a plurality of downstream vanes. The bypass flowpath is fluidly coupled with and downstream of a fan section. The bypass flowpath bypasses a turbine engine core. The upstream vanes are arranged circumferentially about an axis in an upstream vane array. Each of the upstream vanes extends radially across the bypass flowpath. The downstream vanes are arranged circumferentially about the axis in a downstream vane array. The downstream vanes are circumferentially interspersed with the upstream vanes. Each of the downstream vanes extends radially across the bypass flowpath. A first of the downstream vanes is axially offset from a first of the upstream vanes along the axis.

Abstract: A turbine engine is provided that includes a fan section, a turbine engine core, an evaporator, a condenser, a core flowpath and a bypass 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 evaporator is arranged axially along an axis between the fan section and the turbine engine core. The condenser is arranged axially along the axis between the fan section and the turbine engine core. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator and the condenser. The bypass flowpath is fluidly coupled with and downstream of the fan section. The bypass flowpath is radially outboard of and extends axially along the evaporator and the condenser.

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar platform adjacent the first fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg has an end portion that is distal from the spar platform and that protrudes from the second fairing platform. The end portion has a clevis mount. There is a support platform adjacent the second fairing platform. The support platform has a through-hole through which the end portion of the spar leg extends such that the clevis mount protrudes from the support platform. 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.

Abstract: A propulsion system for an aircraft includes a propulsor rotor, an engine core, a housing, a flowpath and a heat exchange system. The engine core is configured to power rotation of the propulsor rotor. The housing includes an inner structure and an outer structure. The outer structure is radially outboard of and axially overlaps the inner structure. The flowpath is downstream of the propulsor rotor and radially between the inner structure and the outer structure. The heat exchange system includes a duct, an exterior orifice, an interior orifice, a flow regulator and a heat exchanger disposed within the duct. The exterior orifice is formed by the outer structure and disposed along an exterior of the housing. The interior orifice is formed by the outer structure and disposed along the flowpath. The flow regulator is configured to selectively fluidly couple the exterior orifice and the interior orifice to the duct.

Abstract: A turbine engine is provided that includes a bypass flowpath, a plurality of upstream vanes and a plurality of downstream vanes. The bypass flowpath is fluidly coupled with and downstream of a fan section. The bypass flowpath bypasses a turbine engine core. The upstream vanes are arranged circumferentially about an axis in an upstream vane array. Each of the upstream vanes extends radially across the bypass flowpath. The downstream vanes are arranged circumferentially about the axis in a downstream vane array. The downstream vanes are circumferentially interspersed with the upstream vanes. Each of the downstream vanes extends radially across the bypass flowpath. A first of the downstream vanes is axially offset from a first of the upstream vanes along the axis.

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 fan section, a turbine engine core, an evaporator, a condenser, a core flowpath and a bypass 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 evaporator is arranged axially along an axis between the fan section and the turbine engine core. The condenser is arranged axially along the axis between the fan section and the turbine engine core. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator and the condenser. The bypass flowpath is fluidly coupled with and downstream of the fan section. The bypass flowpath is radially outboard of and extends axially along the evaporator and the condenser.

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 heat exchanger is provided that a flowpath extending longitudinally through a duct. The flowpath extends laterally within the duct between a first sidewall and a second sidewall. The flowpath extends vertically within the duct between a first manifold wall and a second manifold wall. The first manifold wall is configured to form a peripheral boundary of a first manifold plenum outside of the duct. The second manifold wall is configured to form a peripheral boundary of a second manifold plenum outside of the duct. A plurality of tubes extend vertically across the flowpath and are connected to the first manifold wall and the second manifold wall. Each of the tubes has a bore configured to fluidly couple the first manifold plenum to the second manifold plenum. The tubes include a first tube and a second tube. The first tube is adjacent and angularly offset from the second tube.

Abstract: A tube bundle heat exchanger includes a flow space for a first heat exchange medium; and a plurality of heat exchange tubes for a second heat exchange medium, wherein the plurality of heat exchange tubes extends at least partially across the flow space, wherein the plurality of heat exchange tubes comprises at least a first plurality of tubes having a first diameter and a second plurality of tubes having a second diameter different from the first diameter.

Abstract: A method of fabricating a fiber-reinforced airfoil ring includes providing a mandrel that has a mandrel suction side and mandrel pressure side, and forming an endless braid around the mandrel. The endless braid conforms to the mandrel suction side and the mandrel pressure side. The endless braid is then consolidated with a matrix material. The mandrel is then removed, leaving the consolidated endless braid as a fiber-reinforced airfoil ring that has a suction side wall that extends between inner and outer platforms, a pressure side wall that extends between the inner and outer platforms, and suction and pressure side mate faces along, respectively, edges of the suction side wall and the pressure side wall, and at least one of the suction or pressure side mate faces includes protrusions along a trailing edge.

Abstract: A powerplant for an aircraft includes a turbine engine core, a recovery system and a flowpath. The turbine engine core includes a compressor section, a combustor section and a turbine section. The recovery system includes a condenser and a flow circuit. The flow circuit includes a separator and a treatment device. The recovery system is configured to condense water flowing within the flowpath from a gaseous phase to a liquid phase using the condenser. The recovery system is configured to direct the water in the liquid phase from the flowpath into the flow circuit using the separator. The recovery system is configured to treat a quantity of the water within the flow circuit using the treatment device to provide treated water. The recovery system is configured to provide a quantity of the treated water to the turbine engine core.