When a compressor vane or blade for an engine is used in an environment containing abundant foreign substances, deposits originated from the foreign substances are likely to deposit on surfaces of the vane or blade. The compressor vane or blade according to the present disclosure has a base body of the compressor vane or blade; and a coating covering the base body, which consists essentially of one or more selected from the group of molybdenum disulfide and tungsten disulfide.

A blade containment structure surrounding a fan in a turbofan engine is disclosed. The blade containment structure includes a cellular material to absorb energy and contain fragments of a blade thrown outward; an inner shell; a ductile back sheet spaced radially outward from the inner shell, the ductile back sheet and inner shell cooperating to define a nesting area for the cellular material, wherein the cellular material is bound at its radially inner surface by the inner shell and at its outer surface by the ductile back sheet; and a containment blanket overlaid on the ductile back sheet, the containment blanket being of the type effective to contain fragments of the blade that penetrate through the ductile back sheet.

In accordance with one aspect of the present exemplary embodiment, a molten metal pump comprising a refractory material body defining an elongated chamber is provided. The chamber is configured to receive a shaft and impeller assembly. The chamber includes an open top through which the shaft passes and a bottom inlet. The impeller is located in or adjacent the inlet. The body further defines an elongated passage adjacent to the chamber. An opening provides fluid communication between the elongated passage and the elongated chamber. The elongated passage is in fluid communication with a discharge channel configured to direct molten metal at least substantially perpendicular to an elongated axis of the elongated chamber.

The present application concerns a test engine hood for a turbine engine, such as a double flow turbine. The test hood allows replacement of a flight engine hood during tests on a test bench on the ground where the temperature conditions could damage the flight hood. The test hood includes a tubular wall of carbon-fiber epoxy composite, and metal flanges upstream and downstream. To provide thermal protection, the test hood includes a layer of silicone with a majority of polysiloxane. The layer covers the entire inner surface of the wall to create a barrier. The present application also concerns a method for testing a turbine engine on a test bench, where the turbine engine is fitted with a test casing. The present application also concerns a use of silicone for thermal insulation of the inside of the test hood of the turbine engine on a test bench on the ground.

An article for use in a high-temperature environment that includes a substrate including a superalloy material, a ceramic, or a ceramic matrix composite, and an abradable coating on the substrate, the abradable coating including a rare earth silicate and a dislocator phase, the dislocator phase forms one or more distinct phase regions in the abradable coating and comprises at least one of hafnium diboride (HfB.sub.2), zirconium diboride (ZrB.sub.2), tantalum nitride (TaN or Ta.sub.2N), tantalum carbide (Ta.sub.2C) titanium diboride (TiB.sub.2), zirconium carbide (ZrC), hafnium carbide (HfC), tantalum diboride (TaB.sub.2), hafnium nitride (HfN), or niobium carbide (NbC).

An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.

An airfoil is disclosed. The airfoil may comprise a leading edge, a body portion and a trailing edge formed from a high-modulus plating. The body portion of the airfoil may be formed from a material having a lower elastic modulus than the high-modulus plating. The high-modulus plating may improve the stiffness of the trailing edge, allowing for thinner trailing edges with improved fatigue life to be formed.

A composite component and a plated polymer component are disclosed. The composite component may comprise a body portion formed from an organic matrix composite, a first metal coating applied to a surface of the body portion, and an outer metal layer on the first metal coating that is erosion-resistant. The plated polymer component may comprise a polymer substrate, a metal plating layer applied to a surface of the polymer substrate, and at least one selectively thickened region in the metal plating layer. The at least one selectively thickened region may assist in protecting the plated polymer component against wear and/or erosion.

A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

A continuous flow engine skid component contains a matrix material to improve the overall properties of the continuous flow engine skid component. The continuous flow engine skid component is part of a continuous flow engine skid or is adapted to be part of a continuous flow engine skid, wherein the continuous flow engine skid is adapted to fixate a continuous flow engine in a specified position, wherein the continuous flow engine skid component contains a matrix material, wherein the matrix material contains a nonmetal inorganic or organic matrix.