An airfoil arrangement for a gas turbine engine may include a clearance device using a shape memory alloy movable to provide clearance between an airfoil and one or more other components of the gas turbine engine. The clearance device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

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 combustor for a gas turbine engine includes a combustor liner and a dilution chute integral and conformal with the combustor liner to provide an outlet into the combustor for fuel, wherein the dilution chute has at least one wall with a tapered edge extending into an interior of the combustor.

A seal device is configured so that seal properties can be held over a long period of time. A seal device 1 inserted into and disposed between grooves each formed at first and second components which are adjacent to each other and collectively form a housing structure includes a first seal member inserted into the groove of the first component, a second seal member inserted into the groove of the second component, and a partitioning member extending between the first and second seal members to partition a space between the grooves of the first and second components and arranged movably relative to the first and second seal members.

Provided is a rotating body, including: a shaft; and a compressor impeller including: a main body having an insertion hole, which extends from one end to another end side and is configured to receive the shaft inserted therethrough; a boss portion formed at one end side of the main body; and a joint portion, which is formed on an inner peripheral surface of the insertion hole at the boss portion and is welded to the shaft.

A shaft for a gas turbine engine includes an inner contour with a stiffening rib that defines a stiffened wall thickness related to a nominal wall thickness according to a ratio between about 1.125-2.1.

A free-tipped axial fan assembly features a shroud barrel comprising an inlet, the radius of said inlet at its upstream end being greater than the radius of said inlet at its downstream end. An angle, in a plane including the fan axis, between the surface of said inlet and the direction of the fan axis varies non-monotonically with respect to a surface coordinate which increases with distance along the surface of the inlet.

A sealing apparatus for a turbomachine, including a stator vane component, which includes an inner shroud element and a flow-directing element connected to the inner shroud element. The sealing apparatus includes a sealing component, which has a seal-carrier ring element coupled to the stator vane component. The seal-carrier ring element includes at least one ring body element and at least one projection, which is connected in one piece to the at least one ring body element, protrudes from the at least one ring body element in the radial direction of the sealing apparatus, and is inserted into at least one opening, which extends through the inner shroud element. Other aspects relate to a seal-carrier ring element for a sealing apparatus, and to a turbomachine which includes at least one sealing apparatus and/or at least one seal-carrier ring element.

A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.

A cross-flow fan, and blades of a cross-flow fan are provided. The cross-flow fan includes a rotary shaft; a plurality of blades that extends in a direction parallel to the rotary shaft and having a positive pressure surface and a negative pressure surface; and a connector that connects the rotary shaft and the plurality of blades. At least one protrusion that protrudes in a thickness direction and extends in a longitudinal direction of the plurality of blades is formed on the plurality of blades, and by means of the at least one protrusion formed on a blade surface, a flow separation phenomenon caused by friction with the blade surface is suppressed, thereby reducing noise generated by the cross-flow fan.