A multi-stage charging device includes a shaft that is supported for rotation about an axis. The charging device also includes a first compressor wheel of a first compressor stage. The first compressor wheel is fixed on the shaft. Furthermore, the charging device includes a second compressor wheel of a second compressor stage. The second compressor wheel is fixed on the shaft. Additionally, the charging device includes a turbine wheel of a turbine section. The turbine wheel is fixed on the shaft in a back-to-back arrangement with the second compressor wheel.

A multi-stage charging device includes a shaft that is supported for rotation about an axis. The charging device also includes a first compressor wheel of a first compressor stage. The first compressor wheel is fixed on the shaft. Furthermore, the charging device includes a second compressor wheel of a second compressor stage. The second compressor wheel is fixed on the shaft. Additionally, the charging device includes a turbine wheel of a turbine section. The turbine wheel is fixed on the shaft in a back-to-back arrangement with the second compressor wheel.

An apparatus and method relating to a turbine engine with an annular frame about a centerline defining an axial direction, the annular frame formed from an inner frame wall and an outer frame wall disposed around and radially spaced from the inner frame wall to define an annular airflow passage between the inner and outer frame walls. The annular frame further includes at least two struts each extending between a root at the inner frame wall and a tip at the outer frame wall to define a span-wise direction.

An apparatus and method relating to a turbine engine with an annular frame about a centerline defining an axial direction, the annular frame formed from an inner frame wall and an outer frame wall disposed around and radially spaced from the inner frame wall to define an annular airflow passage between the inner and outer frame walls. The annular frame further includes at least two struts each extending between a root at the inner frame wall and a tip at the outer frame wall to define a span-wise direction.

An apparatus is provided for a gas turbine engine. This engine apparatus includes a shroud, and the shroud includes a wall and a bleed passage. The wall includes an interior surface and an exterior surface. The wall extends circumferentially about an axis. The wall extends depthwise between the interior surface and the exterior surface. The interior surface forms a peripheral boundary of a flowpath that extends along the shroud. The bleed passage includes an inlet orifice and an outlet orifice. The bleed passage extends through the shroud between the inlet orifice and the outlet orifice. The inlet orifice is disposed in the interior surface and fluidly couples the flowpath to the bleed passage. At least a downstream section of the bleed passage circumferentially tapers as the downstream section of the bleed passage extends within the wall towards the outlet orifice.

A decoupled gas turbine engine includes a high spool assembly and a low spool assembly each having a rotational axis that are spaced from one-another. The engine further includes a combustor that may have a centerline spaced from the rotational axes of each spool assembly. Turning ducts of the engine are configured to re-direct airflow from one spool assembly to the next and/or between one spool assembly and the combustor.

A decoupled gas turbine engine includes a high spool assembly and a low spool assembly each having a rotational axis that are spaced from one-another. The engine further includes a combustor that may have a centerline spaced from the rotational axes of each spool assembly. Turning ducts of the engine are configured to re-direct airflow from one spool assembly to the next and/or between one spool assembly and the combustor.

A gas turbine engine comprises a fan at an axially outer location, the fan rotating about an axis of rotation, delivering air into an outer bypass duct, a radially middle duct, and a radially inner core duct. Air from the inner core duct is directed into a compressor, and then flows axially in a direction back toward the fan through a combustor section, and across a core turbine section, and is then directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method of operating a gas turbine engine is also disclosed.

A gas turbine engine comprises a fan at an axially outer location, the fan rotating about an axis of rotation, delivering air into an outer bypass duct, a radially middle duct, and a radially inner core duct. Air from the inner core duct is directed into a compressor, and then flows axially in a direction back toward the fan through a combustor section, and across a core turbine section, and is then directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method of operating a gas turbine engine is also disclosed.

A portable green power system is disclosed that is capable of generating electric power based on green technologies (i.e., environmentally friendly) of high performance, low emissions, and low noise. The portable power system consists of three key design features including a free-floating shaft, an electric motor assisted airblast injector and four concentric channel flows. The engine is partitioned into separate channels or passages for the compressed air, hot gases, recuperation, and the engine case and are organized into four concentric channels for portable design and easy maintenance considerations. The concentric channel design also facilitates fully developed flow in each channel for reduction of vibration and noise. The four concentric channels include turbine concentric channel, compressor concentric channel, recuperator concentric channel and engine case concentric channel. Two-way bypass rings are used for cross flows among these concentric channel flows.