A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend from a first surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.

An aircraft engine, has: an upstream stator having upstream stator vanes circumferentially distributed about a central axis; and a downstream stator having downstream stator vanes circumferentially distributed about the central axis, the downstream stator located downstream of the upstream stator relative to an airflow flowing within a core gaspath of the aircraft engine, a number of the upstream stator vanes being different than a number of the downstream stator vanes, the downstream stator vanes including: a first vane made of a first material, a major portion of a leading edge of the first vane circumferentially overlapped by one of the upstream stator vanes, and a second vane made of a second material having a greater stiffness, strength, and/or ductility than that of the first material, a major portion of a leading edge of the second vane exposed via a spacing defined between two of the upstream stator vanes.

A tool for contouring an airfoil comprises a main body that includes a locator portion and an upper portion. The locator portion includes an engagement surface and the engagement surface is sized and configured to engage an airfoil. The upper portion includes an edge slot sized and configured for placement of an edge of the airfoil into the slot. An abrasive material is applied to the sides of the edge slot. The upper portion and the locator portion are together sized and shaped so that when the edge of the airfoil is disposed in the edge slot and the engagement surface of the locator portion is simultaneously pressed against the airfoil, engagement of the abrasive material with the edge of the airfoil is effective to contour the edge of the airfoil to a preselected and desired shape.

An assembly includes a variable area inlet and an inlet duct. The variable area inlet includes an inlet structure and a center body structure. The inlet structure extends circumferentially about the center body structure with an outer inlet passage radially between the center body structure and the inlet structure. The center body structure includes an outer body and an inner body. The outer body extends circumferentially about the inner body with an inner inlet passage radially between the inner and outer bodies. The inner body is configured to move along a centerline relative to the outer body between a first position and a second position. The inlet duct is fluidly coupled with the outer inlet passage when the inner body is in the first position. The inlet duct is fluidly coupled with the outer inlet passage and the inner inlet passage when the inner body is in the second position.

Disclosed is a cooled airfoil having a hub end and tip, an airfoil height being defined between the hub end and the tip. The airfoil has a leading edge, trailing edge, suction side and pressure side. The airfoil has a first airfoil height section adjacent the hub end and extending towards the tip, wherein, in a meridional view, the leading edge and trailing edge are straight along the first airfoil height section. The airfoil has a second airfoil height section adjacent the tip and extending towards the hub end, wherein, in a meridional view, the airfoil is concavely shaped at the leading edge and is convexly shaped at the trailing edge along the second airfoil height section. At least one cooling channel has a length principally extending along the airfoil height, extends straight in a first cooling channel length section, and is bent in a second cooling channel length section.

A stator blade for a centrifugal compressor having a front portion configured to generate one or more strear-wise vortices in the gas flow around the stator blade in order to avoid and/or delay a detachment of the gas flow from the suction surface of the stator blade especially when the centrifugal compressor is not operating at its operational design speed.

A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

There is disclosed a turbine comprising a stator vane ring 122 downstream of a rotor ring 116 of shrouded rotor blades 118. In vanes of the stator vane ring, an upstream portion of a mean camber line 136 diverges from a profile of the mean camber line at a half-span location, particularly to receive a tip leakage flow over the shrouded rotor blades 118.

A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).