An integrated bladed rotor of a gas turbine engine is provided. The integrated bladed rotor includes a hub having a rotation axis and a radially outer platform relative to the rotation axis, and a plurality of blades extending radially outwardly from the outer platform of the hub. The blades are integrally formed with the hub to define a monolithic component with the hub. Two or more of the blades each include: an airfoil including a groove formed in an outer surface of the airfoil to mitigate crack propagation, and a root fillet providing a transition between the outer platform of the hub and the airfoil.

The present application discloses an impeller for a centrifugal fan and a centrifugal fan. The impeller comprises a support member and several vanes. The support member has an inner wall that defines a hollow portion. The several vanes are arranged inside the hollow portion, each of the several vanes is connected with the inner wall and extends along the axial direction of the support member, and the several vanes are arranged along the circumferential direction of the support member. Each of the several vanes is bent and comprises a front edge, a tail edge, a convex suction surface, and a concave pressure surface, the suction surface and the pressure surface are arranged to oppose each other, and the front edge and the tail edge are arranged to oppose each other, wherein the tail edge is connected with the inner wall of the support member, and wherein several protrusions are provided on the suction surface, and the several protrusions are arranged to be close to the front edge. The protrusions can regulate the flow of a fluid immediately when the fluid contacts the vanes. During the flow regulation process, a large vortex in the fluid can be divided into several small vortices. Such small vortices have smaller friction resistance, and the kinetic energy dissipated from the motion of the small vortices themselves can be partially cancelled out, thereby reducing the noise of the impeller and improving the performance of the centrifugal fan.

In accordance with some embodiments of the present disclosure, a pressure recovery axial compressor blade is provided. The blade may comprise a high pressure surface and a low pressure surface connected at a leading edge and a trailing edge of the blade. Both the high and low pressure surfaces extend span wise from a first end to a second end. At least one of the high and low pressure surfaces has a finite discontinuity in curvature at an intermediate position along the chord of the blade.

A turbine hot gas path (HGP) component includes a body having an exterior surface exposed to a hot gas path, and a cooling circuit defined along an interior surface of the body and fluidly coupled to a coolant source. The cooling circuit includes a plurality of sections spaced from one another but fluidly connected. Each section includes a wall defining at least one cooling passage, and a connector wall coupling between the wall of a first section of the plurality of sections and the wall of an adjacent, second section of the plurality of sections. The wall of the first section and the wall of the adjacent, second section are spaced apart, segregating stress between the sections. The connector wall is more flexible than: the wall of the first section, the wall of the adjacent, second section, and the body, allowing stress relief between the sections.

A method for shaping an aerofoil by: (a) defining an aerofoil having a nominal shape, the nominal shape defined by; a leading edge, a trailing edge, a root and a tip, a span extending from the root to the tip, a pressure surface and a suction surface extending from the leading edge to the trailing edge; a nominal camber line extending from the leading edge to the trailing edge; (b) defining an edge region on one of the pressure and/or suction surface which extends distance of at least 0.1% but no more than 10% of the camber line length from one of the leading edge or the trailing edge of the aerofoil; and (c) adapting the shape of the pressure and/or suction surface within the edge region such that the edge region of the aerofoil achieves an asymmetric profile with respect to the nominal camber line.

An airfoil assembly includes first and second fiber-reinforced composite airfoil rings that each have inner and outer platform sections, a suction side wall extending between the inner and outer platforms, a pressure side wall extending between the inner and outer platforms, and suction and pressure side mate faces along, respectively, edges of the suction and pressure side walls. The suction side mate face of the first fiber-reinforced composite airfoil ring and the pressure side mate face of the second fiber-reinforced composite airfoil ring mate at an interface to form an airfoil that circumscribes an internal cavity. A least one of the suction or pressure side mate faces includes protrusions along a trailing edge of the airfoil. The protrusions define a toothed exit slot for emitting cooling air from the internal cavity.

A rotating airfoil assembly including a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis. Each rotating airfoil of the rotating airfoils includes a leading edge, a trailing edge, a suction surface between the leading edge and the trailing edge, and a pressure surface between the leading edge and the trailing edge. The suction surface and the pressure surface are positioned on opposite sides of the rotating airfoil such that, when airflows over the suction surface and the pressure surface of the rotating airfoil as the rotating airfoil rotates about the rotation axis, the rotating airfoil generates lift. At least one opening is located on one of the suction surface or the pressure surface. The at least one opening is configured to eject air or to draw air into the opening.

An apparatus and method regarding an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The airfoil further comprising at least one cooling passage extending radially within the interior and defining a primary cooling airflow; and at least one cooling hole having an inlet defining a first cross-sectional area, the inlet in communication with the cooling passage, an outlet defining a second cross-sectional area greater than the first cross-sectional area; wherein the primary cooling airflow enters the inlet in a first direction and exits the outlet in a second direction different than the first direction.

A turbine component includes a body having a pair of spaced walls, with at least one of the walls for facing a fluid flow when mounted in a gas turbine engine. There are a plurality of wall cooling passages having a generally boomerang shape such that a peak apex is spaced from the wall and an indent apex is adjacent to the wall, with the plurality of wall cooling passages having interior sides extending from the peak apex toward the wall to define a corner. Outer sides extend from the corners with a component away from the wall and to the indent apex. A gas turbine engine is also disclosed.

A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.