Abstract: A tooling assembly suitable for use in infiltrating a fibrous preform comprises an outer tooling fixture and an inner tooling fixture. The outer tooling fixture comprises a first portion removably attached to a second portion, and a first pair of oppositely disposed windows defined by the first portion and the second portion. Each of the first portion and the second portion comprise a base with a recess. The inner tooling fixture comprises a body defined by at least one portion, the body configured to at least partially surround the fibrous preform, a plurality of holes extending through a thickness of the at least one portion, each hole of the plurality of holes having a length (L) and a diameter (D), and a first neck region engageable with a recess of the first portion or the second portion.

Abstract: A fan drive turbine drives a drive shaft. A compressor section and a turbine section rotate about a rotational axis, with the turbine section positioned in a downstream direction. A fan has fan blades and a fan hub positioned radially within a fan case, with the fan case defining a bypass duct. A fan inlet guide vane case is upstream of the fan blades and a fan exit guide vane case is mounted downstream. The drive shaft is mounted on at least one input drive shaft bearing inwardly of the fan inlet guide vane case. The drive shaft drives a flexible coupling to in turn drive a gear reduction. The gear reduction drives a fan drive shaft to in turn drive the fan hub. At least two fan drive shaft bearings support the fan drive shaft within the fan exit guide vane case. An aircraft is also disclosed.

Abstract: A fan drive turbine drives a drive shaft. A compressor section and a turbine section rotate about a rotational axis, with the turbine section positioned in a downstream direction. A fan has fan blades and a fan hub positioned radially within a fan case, with the fan case defining a bypass duct. A fan inlet guide vane case is upstream of the fan blades and a fan exit guide vane case is mounted downstream. The drive shaft is mounted on at least one input drive shaft bearing inwardly of the fan inlet guide vane case. The drive shaft drives a flexible coupling to in turn drive a gear reduction. The gear reduction drives a fan drive shaft to in turn drive the fan hub. At least two fan drive shaft bearings support the fan drive shaft within the fan exit guide vane case. An aircraft is also disclosed.

Abstract: A tooling assembly suitable for use in infiltrating a fibrous preform comprises an outer tooling fixture with a plurality of outer sidewalls defining an inner volume, each of the plurality of outer sidewalls having an outer wall thickness, and a window extending through the outer wall thickness of at least one outer sidewall of the plurality of sidewalls. The tooling assembly further comprises an inner tooling fixture positioned within the inner volume of the outer tooling fixture, the inner tooling having a plurality of inner sidewalls, each of the plurality of inner sidewalls having an inner wall thickness, and a plurality of holes extending through the inner wall thickness of at least one inner sidewall of the plurality of inner sidewalls. The at least one outer sidewall is positioned adjacent the at least one inner sidewall such that the window overlaps with at least a subset of the plurality of holes in the at least one inner sidewall.

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 propulsion system for an aircraft includes a core engine generating an exhaust gas flow that is expanded through a turbine section, a hydrogen fuel system suppling hydrogen fuel to the combustor through a fuel flow path, a condenser extracting water from the exhaust gas flow, an evaporator receiving a portion of the water extracted by the condenser and generating a steam flow. The steam flow is injected into a core flow path upstream of the turbine section and a cooled cooling air system uses water extracted from the exhaust gas flow for cooling a cooling airflow communicated to the turbine section.

Abstract: A tooling assembly suitable for use in infiltrating a fibrous preform comprises an outer tooling fixture and an inner tooling fixture. The outer tooling fixture comprises a first portion removably attached to a second portion, and a first pair of oppositely disposed windows defined by the first portion and the second portion. Each of the first portion and the second portion comprise a base with a recess. The inner tooling fixture comprises a body defined by at least one portion, the body configured to at least partially surround the fibrous preform, a plurality of holes extending through a thickness of the at least one portion, each hole of the plurality of holes having a length (L) and a diameter (D), and a first neck region engageable with a recess of the first portion or the second portion.

Abstract: A heat exchanger including a primary inlet manifold and a primary outlet manifold supporting at least one tube bundle at opposite ends; said at least one tube bundle including an inlet end piece with each of a first tube, a second tube and a third tube fluidly coupled in series to an outlet end piece; and the first tube, the second tube and the third tube forming one of a coiled tube arrangement and a straight tube arrangement.

Abstract: A tooling assembly suitable for use in infiltrating a fibrous preform comprises an outer tooling fixture with a plurality of outer sidewalls defining an inner volume, each of the plurality of outer sidewalls having an outer wall thickness, and a window extending through the outer wall thickness of at least one outer sidewall of the plurality of sidewalls. The tooling assembly further comprises an inner tooling fixture positioned within the inner volume of the outer tooling fixture, the inner tooling having a plurality of inner sidewalls, each of the plurality of inner sidewalls having an inner wall thickness, and a plurality of holes extending through the inner wall thickness of at least one inner sidewall of the plurality of inner sidewalls. The at least one outer sidewall is positioned adjacent the at least one inner sidewall such that the window overlaps with at least a subset of the plurality of holes in the at least one inner sidewall.

Abstract: A heat exchanger for heat transfer between an external first flow along a first flowpath and a second flow along an internal second flowpath, has: a first manifold; a second manifold; and a plurality of tubes extending from the first manifold to the second manifold and having respective interiors bounding respective legs of the second flowpath. The plurality of tubes comprises a plurality groups of tubes. For each of the groups of the tubes: the tubes of the group have first ends mounted to the first manifold at respective first locations; and the tubes of the group have second ends mounted to the second manifold at respective second locations. From the first manifold to the second manifold, each tube has: a upstream concave first turn; an upstream convex second turn; and an upstream concave third turn; and the second locations are offset downstream along the first flowpath from the respective first locations.

Abstract: A propulsion system for an aircraft includes a gas generating core engine that generates an exhaust gas flow that is expanded through a turbine section. A power turbine engine is forward of the core engine. A propulsor is coupled to the power turbine. A hydrogen fuel system supplies hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from the exhaust gas flow. An evaporator receives a portion of the water that is extracted by the condenser and generates a steam flow. The steam flow is injected into the core flow path upstream of the turbine section. An inlet duct communicates an inlet airflow to the compressor section aft at a location aft of the turbine section. An exhaust duct routes exhaust gas flow through the condenser and into thermal communication with a water flow of water extracted in the condenser in the evaporator.

Abstract: A turbine engine assembly includes a condenser that is at least partially disposed within the core flow path where water is extracted from the exhaust gas flow, an evaporator system that is at least partially disposed within the core flow path that is upstream of the condenser where thermal energy from the exhaust gas flow is utilized to generate a steam flow. An aftercooler provides a cooling flow that is selectively injected into the core flow path upstream of at least the condenser for cooling the exhaust gas flow in response to a parameter that is indicative of an engine operating parameter that exceeds a predefined condition.

Abstract: A vane arc segment includes a platform and an airfoil section that extends in a radial direction from the platform. The airfoil section has a pressure side and a suction side. The platform defines fore and aft axial sides, a core gaspath side, a non-core gaspath side, and first and second flanges that project from the non-core gaspath side. The first and second flanges define, respectively, first and second circumferential mate faces. The first and second flanges each are formed of upturned fiber plies from the platform such that the fiber plies in the first and second flanges are radially-oriented. The first and second circumferential mate faces have, respectively, first and second seal slots that each extend in a ply through-thickness direction across two or more of the fiber plies.