Abstract: An aircraft propulsion includes a core engine section that defines a core flow path where an inlet airflow is compressed, mixed with fuel, and ignited to generate an exhaust gas flow, an inner nacelle assembly that surrounds the core engine section, an outer nacelle assembly that is spaced radially apart from the inner nacelle assembly, and a strut heat exchanger that extends radially between the inner nacelle assembly and the outer nacelle assembly, within the strut heat exchanger a portion of the exhaust gas flow is placed in thermal communication with a second flow for transferring thermal energy.

Abstract: A grid arrayed microtube heat exchanger with vibration dampening support including an upper portion comprising an upper portion support wall having multiple upper portion receivers; a lower portion comprising a lower portion support wall having multiple lower portion receivers; a grid array comprising multiple rows of the lower portion receivers and the upper portion receivers; multiple microtubes supported by the upper portion receivers and the lower portion receivers; a gap located between each microtube; and a support insertable through the gap between the multiple microtubes, the support including at least one cam contacting the microtube, the at least one cam being rigid.

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 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 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: An apparatus is provided for an aircraft powerplant. This apparatus includes a heat exchanger. The heat exchanger includes a frame, a plurality of heat exchanger cores, a first flowpath and a second flowpath. The frame extends circumferentially about an axis. The frame includes a plurality of receptacles within an interior of the frame. Each of the heat exchanger cores is housed within a respective one of the receptacles. The first flowpath extends in a first direction across the heat exchanger and through the plurality of heat exchanger cores. The second flowpath extends in a second direction across the heat exchanger and through the plurality of heat exchanger cores.

Abstract: A heat exchanger assembly includes an inlet manifold that is configured to receive a working fluid, a plurality of microtube assemblies that define corresponding plurality passages for the working fluid and an outlet manifold that is configured to exhaust the working fluid. The plurality of microtube assemblies include a one-piece unitary structure that has a web portion that extends between at least a first microtube portion and a second microtube portion.

Abstract: A propulsion system for an aircraft includes a core engine that generates a core gas flow, a propulsor section that is driven by the core engine and disposed aft of the core engine, a nacelle that surrounds the core engine and the propulsor section, a water recovery system that is disposed in the nacelle, an exhaust duct where the core gas flow is directed radially outward from the core engine to the nacelle, an evaporator assembly that is in thermal communication with the exhaust duct where water is recovered by the water recovery system and is heated to generate a steam flow that is subsequently communicated to the core engine.

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 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 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 propulsion system for an aircraft includes a core engine that generates a core gas flow, a propulsor section that is driven by the core engine and disposed aft of the core engine, a nacelle that surrounds the core engine and the propulsor section, a water recovery system that is disposed in the nacelle, an exhaust duct where the core gas flow is directed radially outward from the core engine to the nacelle, an evaporator assembly that is in thermal communication with the exhaust duct where water is recovered by the water recovery system and is heated to generate a steam flow that is subsequently communicated to the core engine.

Abstract: A steam injected turbine engine includes a core engine section that generates a first gas flow, a burner where an inlet flow is mixed with fuel and ignited to generate thermal energy, and an evaporator where thermal energy from at least the first gas flow is used to transform water into a first steam flow. The first steam flow is injected into a core flow through the core engine.

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.

Abstract: A steam injected turbine engine includes a core engine section that generates a first gas flow, a burner where an inlet flow is mixed with fuel and ignited to generate thermal energy, and an evaporator where thermal energy from at least the first gas flow is used to transform water into a first steam flow. The first steam flow is injected into a core flow through the core engine.

Abstract: A component, and a method of forming a component, including a plurality of representative volume elements, each of the representative volume elements abutting at least one other representative volume element to form the component. Each of the representative volume elements includes at least one dividing structure bound by surfaces offset from a parting surface. The shape and contour of the parting surface defined by a mathematical expression that equals a non-zero constant, the mathematical expression selected to define a triply periodic surface when the expression equals zero.

Abstract: An electrical connector assembly that includes a first connector component that has a housing supporting at least one first exposed contact at an interface surface thereof and has a body portion for terminating a first cable. A second connector component is adapted to slidably receive the first component such that the components are mated and unmated in the same direction. The second component includes a housing supporting at least one second exposed contact at an interface surface thereof and has a body portion for terminating a second cable. When the first component is received in the second component, the components are mated such that the first exposed contact engages the second exposed contact, thereby forming a first electrical connection therebetween and a longitudinal axis of the first cable is spaced from and substantially parallel to a longitudinal axis of the second cable.