A hybrid abradable seal including a stator substrate having an external surface; a casing coupled to the external surface, the casing including radial walls extending radially from the external surface; an abradable material disposed within the casing; the abradable material and the casing being coupled together and configured to resist a deflection responsive to engine gas loads.

An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane formed of a first material, and an edge guard disposed about an edge of the fan blade. The edge guard may include a matrix composite that has a toughness that is greater than a toughness of the first material. The airfoil may include a fan blade or an outlet guide vane. The first material of the airfoil may include a metal alloy and/or a matrix composite. A method of manufacturing an airfoil for a fan section of a turbine engine may include manufacturing an edge guard, attaching the edge guard to the airfoil.

Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of the airfoil. The airfoil also includes opposite leading and trailing edges extending radially along the span. The pressure and suction sides extend axially between the leading and trailing edges. The leading edge defines a forward end of the airfoil, and the trailing edge defining an aft end of the airfoil. Further, the airfoil includes a trailing edge portion defined adjacent the trailing edge at the aft end of the airfoil; a plenum defined within the airfoil forward of the trailing edge portion; and a cooling passage defined within the trailing edge portion proximate the suction side. Methods for forming airfoils for gas turbine engines also are provided.

A method for coating a ceramic matrix composite part with an environmental barrier, the method including a) applying, to a surface of the part, a coating composition including a first powder of a rare earth silicate and a second powder including boron, the coating composition having a ratio R=[mass of the second powder]/[mass of the first powder] of between 0.1% and 5%, and b) sintering the first and second powders to obtain the environmental barrier on the part.

A mold for manufacturing a turbomachine fan casing made of composite material, includes a main axis mandrel around which a fibrous preform of a fan casing is intended to be wound; a plurality of counter-mold angular sectors assembled on the outer contour of the mandrel which are intended to close the mold and to compact the fibrous preform wound on the mandrel; wherein a flat seal with a main elongation axis directed along the main axis is arranged between each angular sector, the flat seal being compressed between two adjacent angular sectors, a first angular sector including a sealing portion passing below a lower face of the flat seal while a second angular sector including a sealing portion passing above an upper face of the flat seal.

A method for manufacturing a metal component includes the following steps: a shell made of a titanium-based material is provided, the shell having a first surface and a second surface remote from the first surface; a covering layer made of a titanium fire-resistant material is produced by additive manufacturing on the shell such that the covering layer at least partially covers the first surface and/or the second surface; and, after the additive manufacturing step, the metal component is heat treated at a temperature of between 200° C. and 1000° C.

A method includes applying a material coating to a surface of a machine component, wherein the material coating is formed from a combination of a hardfacing material, aluminum-containing particles, and a braze material. The method also includes thermally treating the material coating at a temperature to generate an oxide layer comprising aluminum from the aluminum-containing particles, wherein the oxide layer is configured to reduce oxidation of the hardfacing material, and the braze material is configured to facilitate binding between the material coating and the surface of the machine component.

A first cylinder is configured to receive a gas turbine. A second cylinder surrounds an outer circumference of the first cylinder. Retainers extend from the second cylinder towards the first cylinder. Each of the retainers includes a central stalk that extends from the second cylinder towards the first cylinder and a branches extending radially from the central stalk.

A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

A hybrid abradable seal including a stator substrate having an external surface; a casing coupled to the external surface, the casing including radial walls extending radially from the external surface; an abradable material disposed within the casing; the abradable material and the casing being coupled together and configured to resist a deflection responsive to engine gas loads.