A turbine blade for a gas turbine, having a blade root and an aerodynamically curved blade airfoil arranged above the blade root. The blade airfoil has a pressure-side and a suction-side blade wall, together extending from a leading edge, that can receive a flow of working medium, to a trailing edge. A multiplicity of cooling air outlet openings are formed on the pressure-side blade wall, which extend upstream from the trailing edge with respect to the flow direction, and through these openings cooling air that is conveyed through the interior of the blade airfoil can exit. At least one of the cooling air outlet openings has a substantially rectangular or trapezoidal shape with rounded corners. At least the lower corner, pointing towards the leading edge, of the cooling air outlet opening forms a relief notch, which projects outwardly from the rectangular shape, with a rounded notch bottom.

A fan platform for gas turbine engine is provided. The fan platform incudes a body portion and a flow path surface coupled to the body portion. The body portion and the flow path surface define at least a portion of a flow path extending through the engine. The body portion and/or the flow path surface include an impact region including hybrid composite plies including one or more metallic tows. A gas turbine engine including the fan platform and methods for forming the fan platform are also disclosed.

A rotor assembly includes a rotor having a dovetail slot. The dovetail slot includes a plurality of recesses and a first radially innermost surface. A rotor blade includes an airfoil that extends radially outward from a platform and a dovetail that extends radially inward from the platform. The dovetail includes a plurality of projections extending in opposite directions that are received by the plurality of recesses of the dovetail slot. The dovetail further includes a leading edge surface, a trailing edge surface, and a second radially innermost surface. The second radially innermost surface defines a groove from the leading edge surface to the trailing edge surface. The shim is positioned within the groove and between the first radially innermost surface of the dovetail slot and the second radially innermost surface of the dovetail. The shim extends at least partially radially along both of the leading edge surface and the trailing edge surface to secure the rotor blade within the dovetail slot during various operating conditions of the turbomachine.

Methods, apparatus, systems, and articles of manufacture are disclosed to adjust a pitch axis of a blade of an engine. An example blade apparatus includes: a hub to facilitate movement of blades in an engine, the engine having a radial center line; and a trunnion connected to the hub. The example trunnion includes a slot to accommodate a first blade, and at least one of the trunnion or the first blade is positioned with at least one of a tilt or a lean with respect to the radial center line to form a pitch axis offset from the radial center line such that the pitch axis is not parallel to or co-linear with the radial center line. The example hub is to rotate the first blade about the pitch axis.

A method for coating a ceramic matrix composite substrate with an environmental barrier coating includes the steps of: treating a surface of a ceramic matrix composite substrate to adjust wettability of the surface; and applying an aqueous slurry-based environmental barrier coating to the surface. The treating step can be a plasma treatment to remove organic contaminants, and can also be a treatment to modify oxidative state of the surface. The treatment can produce a surface for treatment that is hydrophilic and has a contact angle with aqueous-slurry coating materials of less than 40 degrees.

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

In some examples, article used as a component for a turbine engine that operates in a high temperature environment. The article may include: a ceramic or ceramic matrix composite (CMC) substrate; and a coating on the ceramic or the CMC substrate, wherein the coating defines an outer surface of the article. The coating includes a plurality of surface features defining channels on the outer surface of the article. The channels are configured to modify a flow of molten Calcia-Magnesia-Alumina Silicate (CMAS) over the outer surface of the coating in a gas flow over the outer surface of the article to reduce accumulation of the molten CMAS on the outer surface of the article.

A boundary layer turbomachine can include a housing (10) defining an interior space and having an inlet opening and an outlet opening to facilitate movement of a fluid through the housing (10). The boundary layer turbomachine can also include a rotor assembly (20) disposed in the rotor chamber and configured to rotate about an axis of rotation (1). The rotor assembly (20) can have a plurality of disks (21) spaced apart along the axis of rotation (1) to provide gaps (54) between the disks (21). The plurality of disks (21) can also define an interior opening (26) along the axis of rotation (1). The rotor assembly (20) can have a disk carrier (46) disposed at least partially in the interior opening (26) in support of the plurality of disks (21). The disk carrier (46) can have a fluid passageway (47) exposed to two or more of the gaps (54) between the disks (21). The fluid can pass through gaps (54) between the disks (21) and the interior opening (26) as the fluid moves through the housing (10).

A tip shroud may include a platform to couple to an airfoil having a pressure side and a suction side. A front tip rail and a rear tip rail extend radially from the platform with each including a downstream side, an upstream side, and an origin(s). Each of the downstream side and the upstream side of the rear tip rail and the downstream side of the front tip rail has a shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, Z set forth in a respective table and originating at a selected origin. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, Z values by a minimum rear tip rail X-wise extent expressed in units of distance. The X, Y, Z values are connected by lines to define each respective surface profile.

The invention relates to a housing, wherein the housing has a cover disk having a cylindrical wall and a central receptacle with a hub for supporting a fan having a diagonal fan wheel, wherein a plurality of three-dimensionally curved air guide vanes (S) are arranged about the hub, characterized in that the air guide vanes (S) are materially connected to the cylindrical wall and as a result, the housing is produced in one working step.