A fan includes a frame and an impeller including a hub, a plurality of first blades, a first ring-shaped structure, and a plurality of second blades. The first blades are disposed around the hub. The hub and the first blades are surrounded by the first ring-shaped structure connected with the ends of the first blades, and a central area is structured therebetween. The second blades are connected with an outer rim of the first ring-shaped structure. The frame includes a base, an axle tube portion disposed on the base, and a receiving portion. The impeller is disposed on the axle tube portion. The receiving portion includes plural third blades disposed around the base corresponding to the central area. The first and third blades are matched to each other to be assembled for transforming a tangent velocity into a static pressure to increase the pressure generated by the central area.

A turbine-engine compressor, in particular for an aircraft turboprop engine or turbojet engine, comprising an annular casing and at least one annular row of variable-pitch blades, each blade comprising a radially external end comprising a pivot mounted in an orifice in the casing and connected by a link to a control ring able to pivot axially about its axis with respect to the casing. Each link comprises a first end fixed to the pivot of the blade and a second end mounted so as to be able to pivot on the control ring. The pivot axes of first and second links on the control ring are offset from each other along the axis of the compressor, the second end of the second link being mounted on the ring by a connecting member, allowing a connection of the sliding or annular linear pivot type.

The present disclosure is directed to a method for rejuvenating a damaged coated component of a gas turbine engine. The method includes uninstalling the damaged coated component from the gas turbine engine. The method also includes isolating a first coated portion of the component of the gas turbine engine from a second coated portion of the component. In addition, the method includes simultaneously depositing a first coating material on the first coated portion of the component and a different, second coating material on the second coated portion of the component. The method also includes reinstalling the rejuvenated coated component into the gas turbine engine.

An ash-collecting and exhaust device for a grain dryer has a body, a fan unit, and a driving unit. The body is a hollow barrel, and has an air inlet, an air outlet, and an internal surface being divergent adjacent to the air inlet. The fan unit is rotatably mounted in the body to enable external air to flow into the body via the air inlet and flow out of the body via the air outlet, and has an external surface being obliquely divergent to form an oblique passage between the body and the fan unit. The driving unit is securely mounted on the body, is connected to the fan unit to enable the fan unit to rotate relative to the body to guide the external air flowing into the body.

An airfoil for a turbomachine such as a gas turbine engine includes a switchbacked passage for conveying cooling fluid, and flow-distribution passages in a forward wall so as to direct cooling fluid from the internal passage for back side impingement upon a leading edge of the airfoil. An inner cooling wall forms a passage for discharging the spent cooling air from a trailing edge of the airfoil after impingement, and cools one of a pressure side and a suction side of the airfoil by way of conduction. The switchbacked passage may have a serpentine form.

The present application relates to the compressor stator of an axial turbomachine. The stator comprises an annular row of main stator blades and auxiliary blades each of which are associated with a main blade. The auxiliary blades are located at the trailing edges of the main blades and are in the vicinity of the pressure faces of the main blades. The auxiliary blades are aligned to generate a low-pressure area at the trailing edges of the main blades. Thus, a flow bypassing a main blade by its suction face is sucked in by the low-pressure area when it approaches the trailing edge of the main blade. Stalling is thus avoided and the efficiency of the machine is improved.

A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.

An improved stator assembly is disclosed. The stator assembly may comprise an exit guide vane, an OD ring, and an ID ring. The exit guide vane may couple at one end to the OD ring and at an opposite end to the ID ring. The exit guide vane may comprise a leading edge opposite of a trailing edge. The OD ring and the ID ring may couple to a diffuser assembly of a gas turbine engine. The stator assembly may further comprise an aft OD seal, a forward OD seal, an ID seal, and a diffuser assembly seal to reduce airflow leaks around the stator assembly.

A flowpath component for a gas turbine engine includes a first platform including a vascular engineered lattice structure, a body extending from, and supported by the first platform. The body is configured to at least partially span a flowpath in an installed position and the vascular engineered lattice structure including at least one purge air inlet, and at least one spent air outlet.

A fan assembly includes a fan having an outlet side, a fan duct positioned at the fan outlet side, and a hollow cylindrical chamber positioned within the fan duct, wherein the chamber has two closed ends, a cylindrical side wall, and an inlet port. The dimensions of the chamber are determined to suppress one or more noise frequencies emitted by the fan. In one example, one or more dimensions of a chamber disposed in an outlet duct of an axial fan is automatically adjusted to suppress a noise frequency that is a function of a rotational speed of the axial fan.