The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.

A turbine engine blade having an aerodynamic surface extending a first direction between a leading edge and a trailing edge and in a second direction, perpendicular to the first direction, between a root of the blade and a tip of the blade, the aerodynamic surface being made of a fiber-reinforced organic matrix composite material, and a metallic structural reinforcement bonded by an adhesive joint to the leading edge whose shape it follows and which has over its entire height a substantially V-shaped section with a base extended by two lateral flanks having a thinned profile at free ends directed toward the trailing edge, the adhesive joint being locally supplemented below the free ends of the lateral flanks by an elastomeric polymer introduced in the form of solid particles into the adhesive joint and adhered to the aerodynamic surface and/or the free ends of the lateral flanks during a polymerization phase.

A hybrid electric propulsion system includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid electric propulsion system includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to determine an estimate of hybrid electric propulsion system parameters based on a composite system model and sensor data, determine a model predictive control state and a prediction based on the hybrid electric propulsion system parameters and the composite system model, determine a model predictive control optimization for a plurality of hybrid electric system control effectors based on the model predictive control state and the prediction using a plurality of reduced-order partitions of the composite system model, and actuate the hybrid electric system control effectors based on the model predictive control optimization.

Turbomachine (10) having a contrarotating turbine for aircraft, the turbomachine comprising a contrarotating turbine (22) of which a first rotor (22a) is configured to rotate in a first direction of rotation and is connected to a first turbine shaft (36), and a second rotor (22b) is configured to rotate in an opposite direction of rotation and is connected to a second turbine shaft (38), the first rotor comprising turbine discs that are interleaved between turbine discs of the second rotor, said first shaft (36) being guided by at least two guide bearings (60, 62) mounted between this first shaft and a stator casing, and said second shaft (38) being guided by at least two guide bearings (56, 58) mounted between this second shaft and another stator casing (28).

Fan or propeller vane (1) for an aircraft turbomachine, the vane being made from a composite material and comprising a blade (2) and a base (3), the base being formed by a longitudinal end (41) of a spar (4) which is formed by a fibrous reinforcement formed from threads woven in three dimensions and a portion (42) of which extends inside the blade (2), the blade (2) having an aerodynamic profile which is defined by a skin (5) which is formed by woven threads and which surrounds the portion of the spar, the spar (4) and the skin (5) being embedded in a polymerised resin, characterised in that the portion (42) of the spar comprises projecting longitudinal stiffening members (6) which together delimit spaces (8) for receiving longitudinal inserts (7) which are formed from a honeycomb material.

Disclosed is a turbo machine (10) with counter-rotating turbine for an aircraft, comprising: - a high-pressure body, - a low-pressure counter-rotating turbine (22), - a planetary-type mechanical epicyclic reduction gear (42), - guide bearings (56-62) for the turbine shafts (36, 38), characterised in that said reduction gear (42) and certain of the bearings (60, 62) are housed in a lubrication chamber (86) supplied with oil and comprising dynamic seals (86a-86d), and in that the turbo machine comprises circuits (C1, C2) for pressurising these seals.

An assembly for a turbomachine through which an air flow passes, includes a stator including guide vanes extending radially in relation to a longitudinal axis, at least one inter-vane platform extending between the radially outer ends of two circumferentially consecutive guide vanes, each inter-vane platform including an outer surface that faces the axis, a heat exchanger located downstream of the stator in relation to a direction of circulation of the air flow in the turbomachine during operation, this stator including a heat exchange surface extending in the extension of an inter-vane platform. At least one inter-vane platform located in the upstream extension of the heat exchange surface is provided with at least one turbulence generator on its outer surface.

An article includes a completed fabric structure that has multiple plies of fiber reinforced fabric. A first portion of the fabric structure has a three-directional fiber reinforced configuration and, exclusive of the first portion, a second portion of the fabric structure having a two-directional fiber reinforced configuration. In the three-directional fiber reinforced configuration there are multiple plies that are bound together via a matrix and a plurality of fibers normal through the multiple plies. In the two-directional fiber reinforced configuration the multiple plies are bound to one another via the matrix and not fibers normal through the multiple plies.

A method for controlling a thermal and electrical power plant for setting in motion at least one rotary member of a rotorcraft, the power plant comprising at least one heat engine and an electrical system provided with at least one electric machine. The method comprises: selecting, with a selector, an operating mode chosen from several operating modes; determining a density altitude and comparing, with a controller, the current density altitude and a threshold density altitude; and controlling, with the controller, the at least one electric machine depending on at least the chosen operating mode as well as the comparison and a necessary power to be supplied to the power transmission system.

An airfoil arrangement for a gas turbine engine may include a support device using a shape memory alloy to support and control the airfoil. The support device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.