An additive manufactured article for a gas turbine having a body with two lateral surfaces elongated in a first direction; at least a nested duct housed within the lateral surfaces and elongated in the first direction; a structure so that the nested duct is structurally connected to an attachment within the lateral surfaces, wherein at least the body, the duct and the structure are manufactured by an additive manufacturing process and the structure includes an array of ribs attached to the duct in order to compensate differential elongation along the first direction of the duct with respect to the attachment of the ribs by flexural deformation.

An airfoil includes a stator vane that has a platform with a first radial side and a second radial side, and a platform axial leading end and a platform axial trailing end. An airfoil portion extends radially outwardly from the first side. The platform axial trailing end includes a rear axial face that extends from the first radial side and a radially sloped face that extends from the rear axial face to the second radial side.

In some aspects, the techniques described herein relate to a refrigerant compressor, including: a stator; a rotor configured to rotate with respect to the stator; and at least one step seal between the rotor and the stator, wherein the step seal includes a first tooth and a second tooth extending from the rotor toward the stator, wherein a downstream surface of the first tooth and an upstream surface of the second tooth are arranged at an angle relative to one another, wherein the angle is less than 90.

A rotor disk of a rotor, in particular of a gas turbine, which has serrations, at least on one side, for torque transmission, having a plurality of teeth distributed over the circumference, the tooth flanks of which are aligned opposite with respect to a respective central plane, wherein the tooth flanks have a course that deviates from a radial direction in a cross section perpendicular to the rotor axis.

The invention relates to a heat exchanger of an air circulation channel of a turbomachine, the heat exchanger being configured so as to have fluid to be cooled passing through it and including a plurality of fins protruding from a support surface, the heat exchanger being characterized in that each fin includes a base and a preferably continuous leading face which extends axially from the base in the air circulation direction while tapering from upstream to downstream along an axis parallel with the support surface.

A thrust nozzle, in particular thrust nozzle for a rocket engine, with a convergent wall section, a throat section and a divergent wall section. The divergent wall section has a first region adjacent to the throat section, the wall contour of which region corresponds to a truncated ideal nozzle, and the divergent wall section has a second region facing away from the throat section, which region has a wall contour deviating from the first region.

A gas turbine engine exhaust component is disclosed herein. The gas turbine engine exhaust component includes an annular mixer that extends around a central axis and is formed to include inner lobes that define radially-outwardly opening channels and outer lobes that define radially-inwardly opening channels. A constraint band is added to connect the outer lobes and reduce vibration, deflections, and stresses.