The present application relates to a segmented inner shroud of a low-pressure compressor for an axial-flow turbine engine. The shroud includes an axial tubular wall, and a row of apertures formed in the axial wall. Each aperture has opposing edges situated to either side of a stator vane positioned in the aperture for the purpose of its attachment. The axial wall includes a radial flange which passes through the apertures in the circumferential direction of the shroud, so as to form a mechanical link between the opposing edges of the apertures. This mechanical seal permits the opposing edges to be joined together through each aperture, which improves the rigidity and the sealing. The shroud exhibits an E-shaped profile forming a sandwich structure with the annular sealing fins of the rotor, or sealing lips. The present application also relates to a method for the assembly of stator vanes abutting radially against the transverse radial flange.

A method for patching a damaged polymeric erosion coating (250) on a gas turbine engine component. The method comprises removing a portion of the coating around a damage site (200; 202; 204) and applying a pre-formed coating patch (220).

A continuous flow engine skid component contains a matrix material to improve the overall properties of the continuous flow engine skid component. The continuous flow engine skid component is part of a continuous flow engine skid or is adapted to be part of a continuous flow engine skid, wherein the continuous flow engine skid is adapted to fixate a continuous flow engine in a specified position, wherein the continuous flow engine skid component contains a matrix material, wherein the matrix material contains a nonmetal inorganic or organic matrix.

An acoustic liner can comprise a support layer including a set of partitioned cavities defining a set of cells with open faces, as well as a first and second facing sheet operably coupled to the support layer that overlie and close the open faces. A set of aerogel fillings can be provided within at least some of the set of cells.

The present invention provides an apparatus for providing a balancing weight in a groove on a rotor disk in a gas turbine engine. The apparatus comprises an elongate reservoir for housing a hardenable material and an inflatable balloon in fluid communication with the distal end of the elongate reservoir. An actuator is provided for forcing the hardenable material from the elongate reservoir to inflate the inflatable balloon with hardenable material within the groove on the rotor disk. A sealing device for sealing the inflated inflatable element to form the balancing weight is also provided.

An assembly for a turbojet, the assembly comprising: an outer shroud and an inner shroud that are concentric, the inner shroud being segmented and comprising circumferential clearances between the segments thereof; an annular row of stator vanes connecting the inner shroud to the outer shroud; a drive with a reduction ratio, which drive is intended to be coupled to a fan; and a circuit for cooling and for lubricating the drive, which circuit is configured to heat up at least the outer shroud during the operation of the turbine engine such as to circumferentially reduce the circumferential clearances between the segments.

The present application relates to a stator blade sector configured to be fixed to a housing of an axial turbomachine, the sector having a plurality of blades with platforms juxtaposed, so as to describe an arc of a circle. At least one of the platforms comprises on its outer face a fixing screw and at least one other platform has no fixing screws, the platforms being fixed together at their adjacent edges. The application also relates to a stator or portion of stator having a housing forming a generally circular wall and blade sectors arranged along the wall. The housing includes several parts connected to each other by longitudinal flanges. Platforms with no fixing screws are located opposite the flanges.

A shroud reinforcement is provided for a shroud that is coaxial with and partially surrounds a rotor and that includes tubular and flange sections and a transition section axially interposed between the tubular and flange sections. The shroud reinforcement includes first fiber-reinforced polymer-matrix composite reinforcement elements with fibers extending along an axial dimension of the rotor and being disposed to reinforce the transition section and second fiber-reinforced polymer-matrix composite reinforcement elements with fibers extending along a circumferential dimension of the rotor and being disposed to reinforce the transition section.

A shroud reinforcement is provided for a shroud that is coaxial with and partially surrounds a rotor and that includes tubular and flange sections and a transition section axially interposed between the tubular and flange sections. The shroud reinforcement includes first fiber-reinforced polymer-matrix composite reinforcement elements with fibers extending along an axial dimension of the rotor and being disposed to reinforce the transition section and second fiber-reinforced polymer-matrix composite reinforcement elements with fibers extending along a circumferential dimension of the rotor and being disposed to reinforce the transition section.

An airfoil element including an airfoil having a pressure side and a suction side, an aluminum alloy substrate and a coating system atop the substrate, said coating comprising in at least one location an anodize layer (24) having a thickness (T.sub.A) of 1.0 to 5.0 micrometer, a sealant (36) filling at least 5.0% of porosity in the anodize layer or at least 0.7% of an apparent volume within a height of the anodize layer, a sealant primer (40) filling 50.0% of porosity in the anodize layer or at least 6.5% of an apparent volume within a height of the anodize layer and extending at least flush to the anodize layer, a second primer (44) over the sealant primer having a thickness (T.sub.S) of 5.0 to 50 micrometer and a polymeric coating (48) having a thickness (T.sub.T) of 10.0 micrometer to 1.0 millimeter.