An assembly for a turbomachine extending along an axis includes a combustion chamber having, at its downstream end, a downstream flange having a radially extending part. The assembly further includes a distributor disposed downstream of the combustion chamber and having a platform from which at least one vane extends radially. The platform includes an upstream flange extending radially and delimiting, with the radial part of the downstream flange disposed opposite it. An annular space for the circulation of cooling air opens into the combustion chamber at its radially internal end and has, at its radially external end, means of sealing attached to the distributor.

A tube gallery for a gas turbine engine includes a body. The body includes an external surface. The body also includes a plurality of channels defined in the body. Each channel includes an inlet disposed on the external surface, an outlet spaced apart from the inlet and disposed on the external surface, and a passage extending between and fluidly communicating the inlet to the outlet. The passage of each channel has a non-circular cross-sectional shape. The non-circular cross-sectional shape has a first maximum dimension along a first direction and a second maximum dimension along a second direction orthogonal to the first direction. The first maximum dimension is greater than the second maximum dimension by a factor of at least 1.2.

Provided is a casing deformation amount measuring apparatus for a steam turbine including a casing, a plurality of nuts fixed to an outer surface of the casing, a plurality of bolts individually screwed, at each one side end portion thereof, in the nuts and projecting to an outer side in a diametrical direction of the casing from the outer surface of the casing, and a lagging material held by the plurality of bolts and covering the casing. The casing deformation amount measuring apparatus includes a target mounted on another side end portion of one of the bolts and exposed to the outer side in a diametrical direction of the casing with respect to the lagging material, and a distance meter that is disposed in an opposing relation to the target on the outer side in a diametrical direction of the casing and measures a distance to the target.

A system and method for mitigating thermal loading between engine exhaust structures having different coefficients of thermal expansion. The engine exhaust structure comprises a metallic duct portion, a ceramic duct portion, and a double bipod fitting joining the metallic duct portion to the ceramic duct portion. The double bipod fitting is capable of flexing and taking up the thermal expansion differences between the joined metallic and ceramic ducts across the full temperature spectrum that an engine exhaust structure will experience in service.

A service tube assembly comprises a service tube having a threaded end portion and a ratchet hub spaced from the threaded end portion. The threaded end portion of the service tube is threadably engaged with a mating part. The assembly further comprises a locking member having a cantilever extending from a fixed end held relative to the mating part to a free end. A ratchet pawl is provided at the free end for engagement with the ratchet hub on the service tube.

A gas turbine engine has: an annular gaspath extending around a central axis and defined between a first casing and a second casing; and a variable guide vane (VGV) assembly having: variable guide vanes, the variable guide vanes having airfoils extending between first and second stems at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes; a unison ring rotatable about the central axis, the unison ring operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, and a segmented bushing having bushing segments circumferentially distributed around the central axis, the bushing segments radially supported and axially constrained by the first casing, the unison ring rollingly engaged to the first casing via the bushing segments, the unison ring axially and radially constrained to the first casing via the bushing segments.

A compressor adapted for use in a gas turbine engine includes an impeller, a diffuser, and a deswirler. The impeller is arranged circumferentially about an axis and configured to rotate about the axis. The diffuser is arranged circumferentially around the impeller to receive the air from the impeller. The deswirler is configured to receive the air from the diffuser and to conduct the air into a combustion chamber.

This exit seal is for connecting an exit flange of a combustor and a shroud in a stator blade of a turbine. The exit seal is equipped with: a seal body that extends in a circumferential direction; and a lid member disposed at a circumferential end of the seal body. The seal body comprises one or more recessed sections that are recessed in a radial direction or in an axial direction and extend in the circumferential direction. At a position of the circumferential end of at least one recessed section among the one or more recessed sections, the lid member is disposed so as to overlap, in the axial direction and the radial direction, with a recessed space formed by the one recessed section.

An assembly for mounting an aircraft engine to an aircraft includes an engine casing flange having a first annular wall extending radially to terminate at an annular rim. A second flange of an additional engine component mounted aft of the engine casing includes a second annular wall. An aft mount bracket has an annular body extending uninterrupted about the center axis and a spigot extending axially from the annular body, the spigot extending circumferentially about an entire circumference of the annular body. The aft mount bracket is axially disposed between the engine casing flange and the additional engine component, with corresponding holes in the first annular wall, second annular wall and aft mount bracket being circumferentially aligned, and the spigot radially abutting the annular rim of the engine casing flange.

A fan case assembly is adapted to extend around blades of a fan rotor included in a gas turbine engine. The fan case assembly includes an annular case that extends around an axis, a fan track liner coupled to the annular case and extending circumferentially at least partway about the axis, and a bolting arrangement that couples the fan track liner to the annular case.