HVLP (High Velocity Low Pressure) motor-driven fans and other types of fans, blowers and vacuums take advantage of different thermal and mechanical properties of dissimilar materials used in the motor-driven fans. The dissimilar materials include aluminum for a stacked arrangement of fan wheels and spacers, steel for a shaft that supports the fan wheels and spacers, and a polymeric adhesive. In some examples, the polymeric adhesive is trapped between the aluminum and steels parts. Compared to steel and aluminum, the adhesive has a relatively high coefficient of thermal expansion but relatively low strength such that thermal expansion of the adhesive exerts additional clamping pressure during startup and during high temperature operation. The additional clamping pressure reduces vibration and eliminates other causes of fan or motor failure.

A gas turbine engine component includes a supply cavity and a manifold cavity that shares a common divider wall with the supply cavity. The common divider wall includes inlet metering holes that connect the supply cavity and the manifold cavity. An exterior wall has an exterior surface and an opposed interior surface that bounds portions of the supply cavity and of the manifold cavity. Outlet cooling holes extend through the exterior wall and connect the manifold cavity with the exterior surface. The number of the inlet metering holes is equal to or less than the number of the outlet cooling holes, and at least one of the inlet holes is coaxial with at least one of the outlet holes.

A balancing weight for a rotor blade of a turbine stage of a gas turbine, in particular of an aircraft gas turbine; including a first bent fastening portion that is couplable to an axial leading edge of a shroud of the rotor blade, a second fastening portion that is couplable to an axial trailing edge of the shroud, and a middle portion that joins the first fastening portion and the second fastening portion; the second fastening portion assumes a first position relative to the first fastening portion prior to a mounting of the balancing weight on the rotor blade, and a second position relative to the first fastening portion subsequently to the mounting of the balancing weight on the rotor blade; in the second relative position, the middle portion or/and the second fastening portion being deformed, in particular plastically deformed.

A composite layer system is presented. The composite layer system includes a metallic substrate, a structured surface, and a thermal protection system. The structured surface may be additively manufactured onto the metallic substrate and includes structured surface features formed to project above the metallic substrate. Each of the structured surface features are separated from adjacent structured surface features by grooves. The thermal protection coating may be thermally sprayed onto the structured surface and is bonded to each of the structured surface features.

An axial-flow impeller includes a hub and blades. A tail edge of one blade has recessed portions successively arranged in a direction from a blade root of the blade to an outer edge of the blade. On a reference projection of the impeller on a reference plane perpendicular to a rotation axis of the impeller, a first connection line connects a starting point of a first recessed portion closest to the blade root and an end point of a second recessed portion closest to the outer edge, a second connection line connects a tail edge point of the blade root and the end point of the second recessed portion, one or more of the recessed portions is each partially located at a front-edge side of the second connection line, and remaining one or more of the recessed portions is each completely located between the first and second connection lines.

A film-cooled gas turbine component for a gas turbine has a surface exposed to a hot gas and a number of film-cooling openings open out, which film-cooling openings combined to form at least one row transverse to a flow direction of the hot gas. Each of the film-cooling openings has a duct section and a diffuser section having an upstream diffuser edge, two diffuser longitudinal edges and a downstream diffuser edge. At least two immediately adjacent film-cooling openings, of the respective row have their duct axes of the respective duct sections laterally inclined relative to the local flow direction of the hot gas and their diffuser sections are formed asymmetrically with respect to a projection of the duct axis, such that immediately adjacent corner regions of the respective film-cooling openings are in alignment without the respective diffuser sections making contact with one another.

Provided is a centrifugal compressor impeller capable of improving machine operation efficiency, by making the total pressure distribution of a fluid that flowed into a vaneless diffuser constant. To this end, the provided centrifugal compressor impeller has a plurality of vanes radially provided around a rotating shaft, uses centrifugal force produced by rotating along with the rotating shaft, pumps a fluid (G) taken in from the leading edge side of the vanes to the outside in the radial direction of the rotating shaft from the trailing edge side of the vanes, and thereafter, discharges the fluid (G) into a vaneless diffuser. Furthermore, the edge front end and the edge rear end of the trailing edge are positioned to the outside in the radial direction of the rotating shaft relative to the edge center section of the trailing edge.

A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.

A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.

A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of nested cooling channels in the trailing edge portion of the airfoil permit passage of a cooling fluid from an interior of the turbine component to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a leading edge, a trailing edge portion extending to a trailing edge, and a plurality of nested cooling channels in the trailing edge portion. Each nested cooling channel fluidly connects an interior of the turbine component with an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.