A rocket throat insert including an annular body having a radially inner annular wall portion and a radially outer annular portion. The inner wall portion has a contoured radially inner surface defining a nozzle throat. The outer portion includes an annular buttressing structure supporting the inner wall portion and defining one or more insulation gaps arranged annularly around the inner wall portion. The insulation gaps restrict the radial flow of heat through the annular body.

A turbine engine blade comprising an aerodynamic surface that extends in a first direction between a leading edge and a trailing edge, and in a second direction substantially perpendicular to the first direction between a root and a tip of the blade, and a leading-edge reinforcement comprising a fin partly covering the aerodynamic surface of the blade, characterised in that the fin has a radially outer edge arranged in the vicinity of the tip of the blade and extending between the leading edge and the trailing edge, this radially outer edge comprising an upstream point fitting flush with the tip of the blade at the leading edge and a so-called downstream point separated from the tip of the blade.

A molten metal pump post that includes an elongated rod of a first material that is heat resistant and an inner member at least partially surrounding the elongated rod. The inner member is of a second material. The elongated rod is operable due to a difference in a coefficient of thermal expansion between the elongated rod and the inner member which creates a compressive force.

The present disclosure relates generally to a fan blade assembly. In an embodiment, the fan blade assembly includes an airfoil having a forward edge covered by a sheath. The airfoil and the sheath are made from dissimilar conductive materials. A nonconductive coating is applied the an airfoil contact surface of the sheath before it is bonded to the leading edge of the airfoil.

A metal core for hot-shaping a metal part made out of titanium-based alloy. The metal core presents on an outside surface that is to come into contact with the metal part, a layer of material enriched in metallic carbonitride. The metal core includes an alloy based on nickel or on cobalt, and the nickel- or cobalt-based alloy includes chromium, molybdenum, and/or titanium. A method of fabricating and regenerating the metal core, and also a method of fabricating a metal part using the metal core, are disclosed.

Exhaust redirecting devices are described that are suitable for use in tilt rotor aircraft. Such devices are constructed of light weight material and permit redirection of exhaust gases from turbojet engines of tilt rotor aircraft as nacelles of the aircraft transition between vertical and horizontal flight. Use of a controller permits coordination between exhaust redirection and nacelle position.

A composite vane for a low-pressure compressor of an axial-flow turbomachine, wherein the vane comprises a platform and an aerodynamic airfoil having a leading edge and a trailing edge. The airfoil extends into the primary flow of the turbomachine. The airfoil includes a body extending from the leading edge to the trailing edge and a reinforcement of the leading edge of the airfoil. The reinforcement comprises a reinforcing sheet, which extends from the leading edge to the trailing edge, and which is arranged in the thickness of the body in such a way as to reinforce it. In addition, the reinforcement comprises a shell forming the leading edge and which is integral with the sheet. The sheet is a titanium sheet, and the body includes a composite material having an organic matrix charged with fibers. This configuration improves the rigidity and the resistance to corrosion while lightening the airfoil.

A method of controlling macroscopic strain of a porous structure includes contacting a porous structure with a modifying agent which chemically adsorbs to a surface of the porous structure and modifies an existing surface stress of the porous structure. A device in one embodiment includes a porous metal structure, which when contacted with a modifying agent which chemically adsorbs to a surface of the porous metal structure, exhibits a volumetric change due to modification of an existing surface stress of the porous metal structure; and a mechanism for detecting the volumetric change. Additional methods and systems are also presented.

There is a described an aerofoil component for a turbomachine, the aerofoil component comprising: a central core formed from a metal matrix composite; and an external layer comprising a pressure surface, a suction surface, a leading edge, a trailing edge and a root, the external layer being formed by a metal which covers the metal matrix composite of the central core. Also described is a method of manufacturing such an aerofoil component.

Aspects of the disclosure are directed to a bonding of a first skin and a second skin to a core material, coupling a sheet to the first skin to form with the first skin an enclosure containing the second skin and the core material, exposing the first skin, the second skin, and the core material to heat, and based on the exposition of heat, applying pressure via the enclosure to the first skin to cause the first skin to deform and expand to a shape of a die.