The use of magnesium oxide, reactive alumina and aluminium oxide as a base provides for a new erosion-resistant material upon sintering.

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 gearbox adapted for use with a gas turbine engine and a method for making the same are disclosed herein. The gearbox comprising a housing made from a magnesium alloy, and an aluminum oxide coating on the magnesium alloy housing. The aluminum oxide coating may inhibit corrosion of the housing, and may have a nano-microcrystalline structure that defines an inner region bonded directly to the housing and an outer region spaced apart from the housing.

A blade for a gas turbine engine. The blade having: an airfoil formed from a first material; a protective sheath disposed on a leading edge of the airfoil, the protective sheath being formed from a second material, the first material being galvanically incompatible with the second material and the first material being less noble than the second material; a non-conductive material disposed between the protective sheath and the airfoil so that they are electrically isolated from each other; a sacrificial anode in contact with the blade, wherein the sacrificial anode is formed from a third material that is less noble than the first material such that it will corrode before the first material if the non-conductive material disposed between the protective sheath and the airfoil is compromised and the first material and the second material are no longer electrically isolated from each other.

Said coating structure is provided with: a chemical conversion layer (11), which is formed by chemical conversion coating so as to cover the surface of an impeller body (10) obtained from a magnesium alloy that contains magnesium as the main component and which has a film thickness within a previously determined range; and a plating layer (12) formed so as to cover the chemical conversion layer (11).

The precipitation hardened martensitic stainless steel is characterized by containing, in percent by weight, 12.25 to 14.25% Cr, 7.5 to 8.5% Ni, 1.0 to 2.5% Mo, 0.05% or less C, 0.2% or less Si, 0.4% or less Mn, 0.03% or less P, 0.005% or less S, 0.008% or less N, 0.90 to 2.25% Al, the balance substantially being Fe, and the total content of Cr and Mo being 14.25 to 16.75%. A turbine moving blade and a steam turbine are manufactured by using this martensitic stainless steel.

A method of forming a metal matrix composite (MMC). The method comprises providing a fiber (26) comprising a ceramic material coated with a metal, providing a winding head (12) having a plurality of circumferentially spaced radially extending alternate first and second finger members (18, 20), the finger members each defining a winding surface (22, 24), the winding surface of each first finger member facing a first axial direction, and the winding surface of each second finger member facing a generally opposite axial direction, wherein adjacent winding surfaces (22, 24) of the first and second finger members (18, 20) are spaced in a circumferential direction, and define an axial spacing less than the diameter of the fiber (26), and winding the fiber around the winding head (12) between the winding surfaces (22, 24) of the first and second finger members (18, 20).

An air foil includes a body and a filler. The body may include a chamber formed therein and includes a first metallic material. The filler may at least partially occupy the chamber of the body and may include a second metallic material. The second metallic material may have a comparatively more negative electrode potential than the first metallic material.

The invention proposes a process for maintaining a casting made of magnesium alloy, said casting being a turbomachine accessory gearbox housing or a housing cover, comprising at least one cylindrical surface suitable for receiving a rolling bearing cage, the process being characterized in that it comprises a step (200) that consists in depositing molybdenum on the surface of the casting by plasma spraying.

A rocket engine comprises a combustion chamber and a rocket nozzle that communicates with the combustion chamber. A metal wire supply device supplies a metal wire, which is fuel, to the combustion chamber. A water vapor generator supplies water vapor as an oxidant to the combustion chamber. An ignition device ignites the metal wire in a water vapor atmosphere.