An ejector comprises a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine. The annular wall has a downstream end defining a plurality of circumferentially distributed lobes. The ejector further comprises a secondary nozzle having an annular wall disposed about the primary nozzle, the primary nozzle and the secondary nozzle defining a secondary flow passage therebetween for channeling a secondary flow. The secondary nozzle defines a mixing zone downstream of an exit of the primary nozzle. A flow guide ring is mounted to the primary nozzle lobes. The ring has an aerodynamic surface extending from a leading edge to a trailing edge respectively disposed upstream and downstream of the exit of the primary nozzle. The aerodynamic surface of the ring is oriented to guide the high velocity primary flow into the mixing zone.

A turbo propeller engine comprises a housing circumferentially extending around a longitudinal axis and disposed around a gearbox. The turbo propeller engine includes a propeller outside of the housing and a shaft surrounded in part by the housing and extending along the longitudinal axis. The shaft has a front end and a rear end. The propeller is mounted to the front end. The rear end is in a driven engagement with an output of the gearbox. The shaft is rotatably supported by a first bearing and by a second bearing separated from the first bearing by an axial distance along the longitudinal axis. The first and second bearings are disposed on opposite sides of the gearbox. The first bearing is disposed between the shaft and the housing, the second bearing is disposed between the housing and a component of the gearbox to rotatingly support the component of the gearbox.

A propeller shaft assembly for an aircraft engine includes a shaft having a bore extending through the shaft at a front end thereof, the front end of the shaft having an outer surface facing radially outwardly from the shaft and an inner surface spaced apart from the outer surface and facing radially inwardly to the bore. The shaft has a front flange extending radially outwardly on the outer surface, the front flange having a base merging with the outer surface of the shaft. A sleeve is coupled to the shaft within the bore by an interference fit between the sleeve and the shaft, at least part of the sleeve axially aligned with the front flange. The sleeve axially extends from a front to a rear sleeve end, the rear sleeve end axially offset from the engine side surface of the front flange at the base of the front flange.

An exhaust nozzle assembly for a propulsion system include a primary nozzle, an outer shroud, an ejector nozzle, and an actuator. The primary nozzle extends along an exhaust centerline. The primary nozzle includes a downstream axial end. The outer shroud surrounds the primary nozzle. The ejector nozzle extends axially between a first axial end and a second axial end. The second axial end forms a nozzle exit plane for the exhaust nozzle assembly. The ejector nozzle converges in a direction from the first axial end to the second axial end. The ejector nozzle forms a mixing cross-sectional area between the primary nozzle and the ejector nozzle at the downstream axial end. The actuator is mounted on the ejector nozzle. The actuator is configured to move the ejector nozzle between a first position and a second position, relative to the outer shroud, to control an area of the mixing cross-sectional area.

The present disclosure defines a morphing airfoil having a dynamic flexible skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and deflect in response to control inputs to change a lift force without separate movable control surfaces. The anisotropic skin is attached to underlying structure that is both actively controlled and passively supported. A control system causes the underlying support structure to move to a desired location which in turn causes the skin to bend and/or flex without exceeding a stress threshold and thus vary the lift profile along a span of the airfoil.

An electronic control system (35) for a turbopropeller (2) having a gas turbine engine (20) and a propeller assembly (3) coupled to the gas turbine engine (20), the control system (35) having: a propeller control stage (35a), implementing a closed loop control for controlling operation of the propeller assembly (3) based on a scheduled propeller speed reference (Nr.sub.ref) and a propeller speed measure (Nr); a gas turbine control stage (35b), implementing a closed loop control for controlling operation of the gas turbine engine (20) based on a scheduled reference (Ngdot.sub.ref) and at least a feedback quantity. The control system (35) further envisages an auxiliary control stage (35c), coupling the propeller control stage (35a) and the gas turbine control stage (35b) and determining a limitation of the operation of the gas turbine engine (20), if a propeller speed overshoot is detected, with respect to the propeller speed reference (Nr.sub.ref).

An exhaust assembly for a gas turbine engine includes an outer exhaust case, an inner exhaust case, and a hollow strut. The outer exhaust case forms an outer cavity radially outward of the outer exhaust case. The inner exhaust case is positioned radially inward of the outer exhaust case. The outer exhaust case and the inner exhaust case form a core flow path. The inner exhaust case forms a centerbody. The hollow strut includes a strut body, an inlet, an outlet, and an internal passage. The strut body is connected to the outer exhaust case and the inner exhaust case. The internal passage extending through the strut body from the inlet to the outlet. The inlet is located at the outer radial end. The inlet is in fluid communication with the outer cavity. The internal passage is configured to direct gas from the outer cavity to the outlet.

A routing plate assembly is provided and includes a gearbox having an aft surface, first and second hydraulic components, a routing plate comprising a forward side affixable to the aft surface of the gearbox, an aft side to which the first and second hydraulic components are affixable and a body. The body is formed to define interfacial pathways by which the gearbox and the first and second hydraulic components are communicative.

The invention concerns a power transmission system of a turbomachine, comprising: a speed reducer (12) comprising a sun gear (15) rotationally secured to a power shaft (5) with a longitudinal axis, an outer ring gear (18) rotating a rotor shaft along the longitudinal axis, and a planet carrier (17), and a device (40) for recovering oil ejected by centrifugal effect and comprising an annular gutter (41) for recovering the ejected oil, the gutter being attached to a fixed annular housing (26) and having a recovery chamber (42) and a first wall portion (43) disposed at least partially facing oil ejection means (30) of the speed reducer for directing the oil to the recovery chamber.

According to the invention, the recovery chamber is provided with an inlet opening (45) directed radially outwardly and defined in a plane radially lower than a plane where an outlet port (33) of the ejection means is defined.

An exhaust air energy recovery system configured for efficiently extracting energy from an exhaust stack of a building, duct, mine, server, or the like. The system includes an exhaust stack through which exhaust air moves and a turbine assembly connected to the exhaust stack by one or more legs. The turbine assembly is configured to generate energy from the exhaust air, and the turbine assembly includes a generator configured to convert energy based on the exhaust air; a turbine rotor connected to the generator; and a hub portion interposed between the generator and the lower blade plate.