A guide vane for a variable turbine geometry and a turbine assembly provided with same are described. The guide vane has an outer face that is at least partly concave in design. The inner face opposite the outer face may also be at least partly concave in design. This gives the guide vane a good functional capability when arranged in a vane ring of a turbine, since an overflow through the gap between the guide vane and the neighboring walls is reduced.

A composite material fabrication method includes stacking a plurality of fiber layers and a first binder and curing the first binder to form a three-dimensional structure with a plurality of mesh openings, and filling the plurality of mesh openings with a plurality of fiber filaments of a fiber array and a second binder and curing the second binder. A plurality of first mesh openings of the plurality of mesh openings are connected in a first direction.

A tip for a turbine component, turbine rotor blade or tip of a blade, is disclosed. The tip includes a tip plate configured to be coupled at a tip end of an airfoil chamber; and a tip rail extending radially from the tip plate, the tip rail disposed near or at a periphery of the tip plate. The trip rail includes a cooling structure constituting at least a portion of the tip rail. The cooling structure is in fluid communication with the airfoil chamber, and includes a plurality of repeating, three dimensional unit cells. Each unit cell defines a flow passage that is in fluid communication with the flow passage of at least one other unit cell. The flow passages of the 3D unit cells create a tortuous cooling passage in at least a portion of the tip rail.

A centrifugal fan assembly comprises a blade assembly integrally formed. The blade assembly comprises a plurality of blades integrally formed, wherein each blade of the plurality of blades has a twisted shape with a first portion of a hub end of the each blade facing a first adjacent blade, and a second portion of a outer end of the each blade diagonal to the first portion of the hub end facing a second adjacent blade, a fixing portion integrally connected to the blades. The centrifugal fan assembly comprises at least one opening formed in the fixing portion and a hub plate comprising a recessed portion and a convex portion enabled to couple to the blade assembly. The concave portion is provided to correspond to a shape of the fixing portion and the convex portion is provided to correspond to a shape of the at least one opening.

A diffuser may comprise an inlet and an outlet. The inlet may comprise an arcuate shape. The outlet may comprise an annular shape. The diffuser may transition from the arcuate shape at the inlet to the annular shape at the outlet. The diffuser may comprise a radially inner wall and a radially outer wall disposed opposite the radially inner wall. The radially inner wall and the radially outer wall may partially define a duct.

A compressor blade of a gas turbine includes a root member; an airfoil that is disposed on the root member and includes a first interior wall and a second interior wall forming a hollow space defined between the first and second interior walls; and an organic vibration stiffener (OVS) formed on at least one of the first interior wall and the second interior wall. The OVS is formed by 3D printing performed with respect to a surface of the at least one of the first interior wall and the second interior wall and includes an uneven surface formed on at least part of the at least one of the first interior wall and the second interior wall. The OVS may include a protruded or recessed portion protruding from or recessed into at least part of the at least one of the first interior wall and the second interior wall.

A compressor diffuser for a gas turbine engine includes diffuser pipes having a tubular body including a generally radial portion, a bend portion and a generally axial portion. The generally axial portion has an exit segment extending parallel to the center axis and terminating at a pipe outlet. The bend portion is disposed radially further from the center axis than the exit segment.

An airfoil for a turbine engine, comprising an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction, outlets on the exterior surface, and a cooling air supply conduit within the interior and having a supply passage.

An example diffuser assembly includes a diffuser case, an annular ring, and a retaining tab that is mounted to the annular ring and has an end that engages an inner wall of the diffuser case. The engagement between the second end and the inner wall locks the retaining tab and limits movement of the annular ring along a central longitudinal axis of the diffuser case. Another example diffuser assembly includes a diffuser case, an annular ring, and a snap ring. The snap ring is situated in an annular groove of an inner wall of the diffuser case, and restricts movement of the annular ring along a central longitudinal axis of the diffuser case. A retaining tab is affixed to either the annular ring or the diffuser case, and has an end retaining the annular ring in the annular groove.

A component, such as for a turbine engine, can include an airfoil with an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. The component can also include at least one cooling passage within the interior.