A centrifugal fan is formed from an impeller installed within a casing. The impeller is formed from two plates that are interconnected by a plurality of blades. A duct extends through each blade. At each of its ends, the duct opens at one of the plates. Air enters the fan from through a central opening formed in one of the plates, moves to a medial zone between the plates, and exits the fan at the medial zone's unwalled periphery. Air also crosses the fan by way of the ducts formed within each blade.

In a combustor, and in a gas turbine including the same, a path in which compressed air is mixed with fuel may be increased in each of a plurality of main nozzles. The combustor includes a nozzle casing axially extending in parallel with an extension line (PL); and a plurality of main nozzles to mix and inject compressed air and fuel, the plurality of main nozzles arranged inside the nozzle casing along an imaginary annular line, at least one main nozzle having a center axis inclined at a predetermined angle with respect to the extension line. A central nozzle surrounded by the main nozzles may be disposed in the nozzle casing so as to be parallel to the extension line. Thus, the at least one main nozzle has a path in which the fuel and the compressed air flow that is longer than in the central nozzle.

In a cross section of a flow passage formed to conduct a flow of air from an inside/outside air box to an upper air passage of a scroll casing while the cross section of the flow passage is taken along an imaginary plane which includes an outer edge of an air guide plate and is parallel to a rotational axis of an impeller, a passage section, which is located on one radial side of a separation tube where a nose of the scroll casing is placed, is defined as a first opening section, and another passage section, which is located on an opposite radial side of the separation tube, which is opposite to the nose, is defined as a second opening section. A passage cross-sectional area of the second opening section is larger than a passage cross-sectional area of the first opening section.

A turbine rotor blade is additively manufactured and includes an airfoil body with a radially extending chamber for receiving a coolant flow, a tip end at a radial outer end of the airfoil body, and a shank at a radial inner end of the airfoil body. The radially extending chamber extends at least partially into the shank to define a shank inner surface. An integral impingement cooling structure is within the radially extending chamber. The integral impingement cooling structure allows an exterior surface of a hollow body thereof to be uniformly spaced from the airfoil inner surface despite the curvature of the chamber. The turbine rotor blade has impingement cooling throughout the blade.

A turbine rotor blade is additively manufactured and includes an airfoil body with a radially extending chamber for receiving a coolant flow. A platform extends laterally outward relative to the airfoil body and terminates at at least one slash face. A cooling circuit is within the platform and is in fluid communication with a source of the coolant flow. Cooling passage(s) are in the platform and in fluid communication with the cooling circuit. The cooling passage(s) extend in a non-linear configuration from the cooling circuit to exit through the at least one slash face of the platform, providing improved cooling compared to linear cooling passages.

A turbine rotor blade root is additively manufactured and includes a shank having a radially extending chamber defined therein. A blade mount is at a radial inner end of the shank. The blade mount has a hollow interior defined therein with the hollow interior in fluid communication with the radially extending chamber. A lattice support structure is disposed within the hollow interior of the blade mount.

A gas turbine engine component includes a vane arc segment that defines an axis. The vane arc segment includes an airfoil section and first and second platforms. The airfoil section has a first radial end, a second radial end, a first side, a second side, a leading edge, and a trailing edge. The airfoil section has associated characteristics, including a center of pressure and an aerodynamic load vector through the center of pressure. The first platform defines a first side chevron face that has a leading leg and a trailing leg that meet at an angle. The leading leg is elongated along a centerline that is non-axially oriented with respect to the axis, the leading leg meets the leading face at a leading first side corner. The leading first side corner is located outside of the aerodynamic load vector relative to the leading edge of the airfoil section.

Rotor blades and turbomachines are provided. A rotor blade includes a platform and an airfoil extending radially from a root proximate the platform to a tip. The airfoil includes a leading edge and a trailing edge. The airfoil further includes a pressure side surface extending between the leading edge and the trailing edge. The airfoil also includes a suction side surface disposed opposite the pressure side surface and extending between the leading edge and the trailing edge. The leading edge, the trailing edge, the pressure side surface, and the suction side surface collectively define a first profile at the tip and a second profile radially inward from the tip. The first profile includes a suction side overhang, a pressure side overhang, and a pressure side underhang relative to the second profile.

A rotating machine includes a plurality of rotors. Each of the rotors includes a rotor bore protruding radially inward from a platform. A ring shaped cover plate is interfaced with each rotor bore via at least one snap. The at least one snap includes a first arm extending from the cover plate and having a convex facing contact surface, and multiple second arms extending axially from each rotor bore and having contact surfaces facing the convex surface.

A turbocharger turbine wheel can include a hub that includes a rotational axis, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system that includes a radial coordinate (r) and an azimuthal coordinate (Θ) in a direction of intended rotation about the rotational axis; and blades that extend outwardly from the hub, where each of the blades includes a leading edge and a trailing edge, where the leading edge includes a lower axial point defined by a first theta angle and an upper axial point defined by a second theta angle, where the first theta angle is greater than the second theta angle with respect to the direction of intended rotation of the turbine wheel.