An upstream rail of a turbine engine turbine casing, which includes a casing body extending along a longitudinal axis, includes a base including a radial face, extending substantially radially from the casing body, a plate including an upper face, extending substantially along the longitudinal axis, a connection portion between the base and the plate, including a concave face connecting the radial and upper faces, the concave and radial faces extending on either side of an edge. The upstream rail is repaired through a method including covering a surface with a solder, the surface including the upper and concave faces such that the solder extends until the edge, and machining the covered surface, in a single action, in a direction toward the radial face, so as to reshape the surface, wherein the machining of the covered surface is performed on a portion of the radial face.

A system for retaining stators and reducing air leakage in a gas turbine engine having an axis includes a stator having an inner platform, an outer platform, a low pressure side, a high pressure side, and at least one foot, and designed to turn air. The system also includes a case positioned radially outward from the stator and having at least one recess designed to interface with the at least one foot to resist movement of the stator relative to the case. The system also includes a bladder positioned between the outer platform of the stator and the case and designed to receive pressurized fluid having a greater pressure than ambient pressures experienced at the low pressure side of the stator and to further resist movement of the stator relative to the case in response to receiving the pressurized fluid.

A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection is between the fan case and the core engine includes three triangular-frame connecting members rigidly connected to the fan case at a fan case connection point, and to the core engine at a core engine connection point. The triangular-frame connecting members each are defined by two rigid legs which extend between the fan case and to the core engine, along directions each have a component extending radially inwardly and a component in opposed circumferential directions to each other. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

Methods, apparatus, systems, and articles of manufacture are disclosed to implement a stator plenum with collet seal. The stator plenum for a gas turbine engine includes an outer shell circumscribing a centerline axis, a first end of the outer shell coupled to an engine casing at a first coupling, the first coupling to form a first seal, a second end of the outer shell coupled to the engine casing at a second coupling, the second end formed by a thickened portion of the outer shell, the second coupling to form a second seal, and a cavity formed by the outer shell, the cavity to contain cooling flow to reduce a temperature of a turbine.

A turbine nozzle assembly for use in a turbine engine is provided. The assembly includes an inner barrel and a turbine nozzle support ring. The inner barrel has a forward end and an aft end. The turbine nozzle support ring includes an annular body that defines a forward end, an opposite aft end, an inner surface, and an opposite outer portion. The forward end of the annular body is coupled to the aft end of the inner barrel. The annular body includes a first arcuate segment and a second arcuate segment removably coupled to the first arcuate segment. The first arcuate segment has a first arcuate length and the second arcuate segment has a second arcuate length. The second arcuate length is shorter than the first arcuate length.

A shroud segment including a forward radial wall, an aft radial wall and at least one interlocking subcomponent. The forward radial wall, an aft radial wall and the at least one interlocking subcomponent are each formed of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The shroud segment further including an interlocking mechanical joint joining each of the forward radial wall and the aft radial wall to the at least one interlocking subcomponent. Methods are also provided for joining the forward radial wall and the aft radial wall to the at least one interlocking subcomponent using an interlocking mechanical joint.

The composite seal structure includes a carrier ring and a seal element housed in an annular groove formed between a circumferential outer wall and two side walls of the carrier ring. The seal element has a first region in surface-to-surface contact with the annular groove and a second, seal-ing region protruding from the annular groove. A fastening arrangement couples the seal element and the carrier ring to one another. The fastening arrangement comprises a plurality of fastening pins circumferentially arranged around the axis of the carrier ring. Also disclosed is a method for manufacturing the seal structure.

A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

The present invention relates to a housing arrangement for a turbomachine, comprising a support element, which is configured to bear a shaft, and a housing, which is centered at the support element. The housing is composed of an inner housing and an outer housing fastened at the support element, the housings being connected to each other by at least one connecting strut. A press fit is provided between the support element and the inner housing, in order to center the inner housing at the support element.

A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction. An inner core engine has an inner core engine housing surrounding a compressor section, including a low pressure compressor. A rigid connection between a fan case and the inner core engine includes A-frames rigidly connected at a connection point to the fan case. Fan exit guide vanes rigidly connect to the fan case, and to the inner core engine. A fan intermediate case is positioned forward of a first rotor stage in the low pressure compressor. A rigid structure is connected to the inner core engine and to the fan exit guide vanes. The rigid structure defines a structure moment stiffness. The fan intermediate case defines an intermediate case moment stiffness. A ratio of the structure moment stiffness to the intermediate case moment stiffness is between 5 and 15.