Various embodiments of an airfoil and machines with airfoils are disclosed. The airfoils include a thicker leading airfoil portion and a thinner trailing airfoil portion. In one embodiment, the leading airfoil portion is formed by bending a body of the airfoil back toward itself. In another embodiment, the leading airfoil portion has a solid geometry and includes two elliptic surfaces. To prevent detachment of airflow, the leading airfoil portion includes at least two arc portions or surfaces that act to direct the airflow down to the trailing airfoil portion in a manner that stabilizes vortexes that may form in the region of changing thickness.

An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with a metering portion with a constant cross-sectional area and a cross-sectional shape having a maximum height that is offset relative to a longitudinal centerline of the metering portion; and a diffuser portion extending from the metering portion to the external surface of the body.

An airfoil is disclosed herein. The airfoil may include a leading edge, a trailing edge, a suction side defined between the leading edge and the trailing edge, and a pressure side defined between the leading edge and the trailing edge opposite the suction side. The pressure side may include a concave profile about the trailing edge that varies from a profile of a remainder of the pressure side.

Aspects of the disclosure generally relate to a turbine center frame for a turbine engine through which a flow path extends. The turbine center frame can include an inner wall radially spaced from an outer wall, with the inner and outer walls extending between an inlet and an outlet, and with the outlet downstream of the inlet with respect to the flow path. A set of circumferentially-spaced airfoils can extend between the inner wall and the outer wall.

A turbine blade that includes an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade further may include a rib configuration that partitions the chamber of the airfoil into radially extending flow passages. A first flow passage may include a first side on which turbulators are positioned, wherein each of the turbulators comprises a canted configuration.

In a centrifugal compressor including an impeller rotatably disposed in a housing, the housing includes a shroud wall and a hub wall, which define a diffuser passage communicating with an outlet of the impeller. The diffuser flow passage includes a pinched part configured such that the shroud wall is closer to the hub wall radially outward of the centrifugal compressor from the outlet of the impeller, and a parallel part communicating with the pinched part on a radially outer side of the centrifugal compressor than the pinched part, the parallel part being configured such that the shroud wall and the hub wall are parallel to each other. The shroud wall has a surface facing the impeller and the hub wall, the surface having a cross-sectional shape where a tangent line exists at any position in a cross-section including an axis of the impeller.

A nozzle vane for a variable geometry turbocharger satisfies 0.45<(Xp/L)≤0.60, where L is a chord length of the nozzle vane, and Xp is a distance between a leading edge of the nozzle vane and a rotation center of the nozzle vane.

An assembly is provided for a turbine engine. This assembly includes a static structure, a conduit and a conduit bracket. The static structure includes a port. The conduit extends longitudinally through the port. The conduit bracket couples the conduit to the static structure. The conduit bracket includes a base mount, a conduit mount and a damper. The base mount is attached to the static structure. The conduit mount is attached to the conduit. The damper is between the base mount and the conduit mount. The damper includes a first leg, a second leg and a web. The first leg projects laterally out from the base mount. The second leg projects laterally out from the conduit mount. The web is longitudinally between and connected to the first leg and the second leg.

An airfoil for disposition and exposure to flow in a hot gas duct of a turbomachine is provided. The airfoil has a suction-side wall and a pressure-side wall with respect to its exposure to the flow in the gas duct, the side walls converging in an upstream end region toward a leading edge and converging in a downstream end region toward a trailing edge. The airfoil further has a cavity structure therein which is enclosed between an inner wall surface of the suction-side wall and an inner wall surface of the pressure-side wall when viewed in a cross-sectional plane axially parallel to a longitudinal axis of the turbomachine. When viewed in the cross-sectional plane, at least one of the inner wall surfaces, normalized to a mean camber line of the airfoil as a reference, extends with a change in curvature into at least one of the end regions in such a way that a clearance width of the cavity structure is increased at the at least one end region.

A flexible seal is used to seal between two adjacent gas turbine components. The flexible seal includes at least one metal ply having a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially, and optionally radially, offset from the forward end. A plurality of relief cuts is defined through the at least one metal ply between the forward end and the aft end to increase flexibility and improve sealing in seal slots that are radially offset from one another.