A gas turbine has blades. A blade may have a leading edge; a trailing edge; a pressure side and a suction side, which extend between the leading edge and the trailing edge. The blade has, along the leading edge, a leading edge profile with profile portions, each of which, along its profile portion length, transitioning, proceeding from a depression, into an elevation via a first transition portion and back into a next depression via a second transition portion. An apex of the elevation of a profile portion is arranged in an asymmetric manner in relation to the profile portion length, in such a way that the first transition portion has a first transition length and the second transition portion has a second transition length. The first transition length and the second transition length are different lengths.

A fan blade apparatus for use in a high-volume, low-speed fan wherein the fan blade includes a body portion, a leading edge portion and a trailing portion. The fan blade coupled to an electric motor configured to rotate in an intended direction wherein the leading portion of the fan blade is at the forefront of the rotation of the blade. The leading edge portion of the fan blade includes a series of steps extending along the length of the leading edge. The stepped configuration creates turbulent air flow when the electric motor rotates in the intended direction.

The invention relates to a housing, wherein the housing has a cover disk having a cylindrical wall and a central receptacle with a hub for supporting a fan having a diagonal fan wheel, wherein a plurality of three-dimensionally curved air guide vanes (S) are arranged about the hub, characterized in that the air guide vanes (S) are materially connected to the cylindrical wall and as a result, the housing is produced in one working step.

A device for applying at least one coating material to a substrate surface. The device includes a flexible base plate having a toothing which is mounted on at least one side of the flexible base plate as a toothed side, a channel which is arranged parallel to the toothed side, and at least one sealing lip which is arranged on a side of the channel which faces away from the toothed side.

An air conditioner of the present disclosure includes a base case configured to include a suction port through which air is sucked and accommodate a filter therein, a tower case configured to be disposed above the base case and to include a discharge port through which the air sucked from the suction port is discharged, and a heater configured to be disposed inside the tower case to heat the air.

A method for removing a component fixed to an aeronautical part, the aeronautical part comprising a first material, and the component comprising a second material different from the first material, the method comprising steps of determining the thicknesses of the component as a function of the position on the component, and of removing the component by means of a pressurized water jet moving over the component as a function of the thicknesses determined in the determination step.

A process for manufacturing a blade made of composite material for a turbomachine is provided. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: a) placing a preform, made by three-dimensionally weaving fibers, in a mold, a polymerizable adhesive being inserted between the sheath and the edge of the preform; and b) injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying, wherein the resin is injected within a time interval during which the adhesive reaches a freezing point.

An impeller includes: a disk which is supported so as to be rotatable around an axis and which includes an outer peripheral surface expanding toward an outside in a radial direction of the disk as it goes to a downstream side in an axial direction of the axis; blades which are arranged on the outer peripheral surface of the disk at intervals in a circumferential direction of the disk; and a cover which is disposed at a position facing the outer peripheral surface of the disk so as to cover the blades. A leading edge of each of the blades includes: a straight portion which extends toward the downstream side in the axial direction of the axis as it goes to the disk from the cover; and a protrusion portion close to the disk and which is protruded from an extension of the straight portion.

Airfoil for gas turbine engines are described. The airfoils have internal walls and internal cavities. A leading edge cavity is defined within the airfoil body along a leading edge and a leading edge feed cavity is arranged aft of the leading edge cavity. A bent leading edge rib is arranged between the leading edge cavity and the leading edge feed cavity. A main body cavity is arranged aft of the leading edge feed cavity and defined at least in part by two interior ribs that define a part of the leading edge feed cavity. The main body cavity is fluidly connected to the leading edge feed cavity by an interior fluid connection through the intersection of the two interior ribs. A shield cavity is arranged to thermally shield the leading edge feed cavity from heat pickup along the suction side of the airfoil body.

The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.