A method of assembling a ceramic matrix composite (CMC) component is provided. The method includes assessing which portions of the CMC component require relatively high-temperature capability and which portions require at least one of strength, thickness and increased thermal conductivity, making the portions that require the relatively high temperature capability with chemical vapor infiltration (CVI), making the portions that require the at least one of strength, thickness and increased thermal conductivity with melt infiltration (MI) and combining the portions that require the relatively high temperature capability with the CVI and the portions that require the at least one of strength, thickness and increased thermal conductivity with the MI.

A tool for installing segments of a coupling having male and female couplers drivingly engaged to one another by the segments, the tool has: a coupler-engaging section engageable to the a female coupler of the couplers for radially supporting the tool relative to the female coupler about a rotation axis of the coupling; and a peripheral wall secured to the coupler-engaging section and extending circumferentially around the rotation axis, a diameter (D2) of the peripheral wall selected to allow insertion of the segments between the female coupler and the peripheral wall, the peripheral wall defining an abutting surface against which radially inner ends of the segments abut during insertion of the segments between the female coupler and the peripheral wall.

An internal structure of a primary exhaust duct of a turbomachine, which has a primary wall allowing air to pass through orifices and forming an internal surface of the primary exhaust duct, an interior skin arranged inside the primary wall, and at least one separator of which a first edge region is attached to the interior skin and which has two geometries. A change from the first geometry to the second takes place when the temperature of the separator exceeds a first temperature, and the change from the second to the first takes place when the temperature of the separator drops below a second temperature. The coefficient of expansion of the separator is greater than that of the interior skin. The variation in the geometry of the separators depending on the temperature of the engine eases assembly at ambient temperature due to the compression of the separators.

A gas turbine apparatus includes a turbine configured to be driven by a combustion gas from a combustor, an exhaust passage, an extraction line configured to extract a fluid from a combustor casing, a cooling part disposed in the extraction line and configured to cool the fluid, a return line for returning the fluid from the cooling part to an inside of the combustor casing, the return line being connected to the extraction line downstream of the cooling part, a bypass line for introducing the fluid from the cooling part to the exhaust passage by bypassing the turbine, the bypass line branching from the return line, and a communication state switching part for controlling a communication state between the extraction line and the combustor casing via the return line, and a communication state between the extraction line and the exhaust passage via the bypass line.

A vibration damping element for a vibration damping system for a turbine nozzle or blade includes an elongated body and a wire mesh member that surrounds the elongated body. The wire mesh member has a first outer dimension in an inoperative state and a second, larger outer dimension in an operative state. In the operative state, the wire mesh member frictionally engages with an inner surface of a body opening in the turbine nozzle or blade to damp vibration. In the inoperative state, the wire mesh member slides freely in the body opening in the turbine nozzle or blade. A retention system includes a retention member on the elongated body that fixes the wire mesh member relative to a length of the elongated body in the operative state in the body opening of the turbine nozzle or blade.

A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

The invention relates to an assembly comprising a turbomachine casing (7) and a nozzle made of ceramic matrix composite material having a blade (21), the frontside and backside surfaces of which delimit an internal cavity, and which is connected at its radially external end by a connecting part (31) of the nozzle to the casing (7), said connecting part (31) extending substantially radially outwards, the blade (21) and said connecting part (31) being formed in one piece, said assembly being characterized in that the connecting part (31) is fastened to a first radial wall (51) integral with the casing (7) by fastening means (53).

A turbomachine includes a first housing member having a first journal bearing portion and a first radial control surface. The turbomachine also includes a second housing member with a second journal bearing portion and a second radial control surface. The second radial control surface has an interference fit with the first radial control surface that radially aligns the second journal bearing portion and the first journal bearing portion along a common axis.

The present invention relates to a rotor blade arrangement for a turbomachine, with a rotor blade which has a sealing tip radially on the outside, and with a seal arrangement, wherein the seal arrangement forms a radially inwardly open cavity, in which the sealing tip is arranged, to which end the seal arrangement has a first sealing element, namely a first seal carrier with a first run-in coating, and a second sealing element, wherein the first run-in coating delimits the cavity radially on the outside, and the second sealing element delimits the cavity in an axial direction, and wherein the first and the second sealing element are assembled.

A turbofan gas turbine engine includes, among other things, a fan section including a fan hub and an outer housing, the fan hub including a hub diameter supporting a plurality of fan blades, a turbine section including a fan drive turbine, and a geared architecture that interconnects the fan drive turbine and the fan hub, the geared architecture including a gear volume.