A gas turbine spacer disk includes a disk portion, a rim portion, a first fillet, and a second fillet. The disk portion is disposed about a rotational axis. The rim portion is disposed about the disk portion. An outer face of the rim portion defines a plurality grooves extending circumferentially about the rotational axis. The first fillet transitions from the rim portion to a first side of the disk portion. The second fillet transitions from the rim portion to a second side of the disk portion. The plurality of grooves includes a pair of first grooves having a first diameter and a pair of second grooves having a second diameter that is less than the first diameter. A first one of the first grooves overlaps in an axial direction with the first fillet. A second one of the first grooves overlaps in the axial direction with the second fillet.

The present disclosure provides methods, assemblies, and systems for power production that can allow for increased efficiency and lower cost components arising from the control, reduction, or elimination of turbine blade mechanical erosion by particulates or chemical erosion by gases in a combustion product flow. The methods, assemblies, and systems can include the use of turbine blades that operate with a blade velocity that is significantly reduced in relation to conventional turbines used in typical power production systems. The methods and systems also can make use of a recycled circulating fluid for transpiration protection of the turbine and/or other components. Further, recycled circulating fluid may be employed to provide cleaning materials to the turbine.

The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies.

An airfoil assembly for use in a turbine of a gas turbine engine includes an airfoil that extends radially relative to an axis. The airfoil includes an inner surface that defines a cooling cavity that extends radially into the airfoil and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a section side of the airfoil. The airfoil assembly further includes features for increasing the heat transfer coefficient of the airfoil.

The present disclosure provides methods, assemblies, and systems for power production that can allow for increased efficiency and lower cost components arising from the control, reduction, or elimination of turbine blade mechanical erosion by particulates or chemical erosion by gases in a combustion product flow. The methods, assemblies, and systems can include the use of turbine blades that operate with a blade velocity that is significantly reduced in relation to conventional turbines used in typical power production systems. The methods and systems also can make use of a recycled circulating fluid for transpiration protection of the turbine and/or other components. Further, recycled circulating fluid may be employed to provide cleaning materials to the turbine.

There is disclosed a fan track liner assembly 53 for a containment arrangement 50 of a gas turbine engine, the assembly 53 comprising a cellular reactive impact structure 60, wherein cells of the reactive impact structure 60 contain a reactive material having shear-thickening or shear-stiffening properties; whereby the reactive impact structure 60 is compliant during assembly to accommodate geometrical non-compliance in the fan track liner assembly.

A turbomachine vane includes a blading made of composite material with fibrous reinforcement densified by a matrix and an integrated metal leading edge, the blading extending in a longitudinal direction, the leading edge being formed by a metal foil overmolded onto the blading, the foil having a lower wing and an upper wing which extend respectively on the lower and upper faces of the blading while matching an aerodynamic profile of the vane. One of the lower wing and the upper wing has a positioning portion extending in the longitudinal direction, the portion having a flat inner face and an increasing thickness away from the leading edge, and being housed in a correspondingly shaped groove in the blading.

Methods and masks for manufacturing component of gas turbine engines are described. The methods include applying a mask to a protected surface of the component, the component having a designated surface to be treated by a shot peen operation. The mask includes a full masking portion configured to prevent a shot peen media from impacting the protected surface. A masking control region is arranged around the designated surface. The masking control region is configured to control an amount of force imparted to the component by shot peen media during the shot peen operation, wherein the masking control region extends from the full masking portion to the designated surface. The designated surface is shot peened with shot peen media to form a compressive stress region within the component proximate the designated surface and a tapering transition of compressive forces within the component proximate the masking control region.

A method for making a composite article comprises securing a layup over a form. The layup including a plurality of dry intermediate reinforcement plies wrapped around an inner reinforcement ply. Resin is infused into the layup under vacuum. The resin-infused layup is consolidated under pressure and cured.

An aviation turbine engine having at least one unducted rotary propeller having a plurality of blades, each blade including: a blade body made of composite material including fiber reinforcement densified by a matrix, the fiber reinforcement of the blade body presenting three-dimensional weaving, the body extending between a leading edge and a trailing edge, and a protective fitting for protecting the leading edge and made of composite material having fiber reinforcement densified by a matrix, the fitting being adhesively bonded onto the leading edge of the blade body, the fitting being formed from a dry fiber preform injection molded with a densifying resin, and a polyurethane film for providing protection against erosion covering the blade body and the fitting.