A vane assembly includes a platform. A vane cover is arranged adjacent the platform. The vane cover has a protrusion that provides a spring land. The spring land is arranged at an angle relative to the vane cover. A spring assembly has a plunger. The plunger is in contact with the spring land.

A vane segment includes a blade ring, a plurality of vanes, and a caulking member. The blade ring includes a blade ring groove and a storage space forming portion. The blade ring groove includes a convex portion projecting from a second groove side surface of the blade ring groove to the first side. The storage space forming portion, in combination with an outer shroud, forms a storage space into which the caulking member enters. The caulking member is accommodated within the storage space, contacts with the blade ring groove and the outer shroud, and is exposed from an inner opening of the storage space.

A turbomachinery stator apparatus includes: a compressor casing including a casing wall defining an arcuate flowpath surface and an opposed backside surface, the flowpath surface defining at least two spaced-apart rotor lands, a stator vane row of stator vanes disposed inside the compressor casing, wherein the casing wall includes a heat shield positioned outboard of the rotor lands immediately upstream or downstream of the stator vane row, and wherein a) the casing wall includes the heat shield and b) the stator vanes form a single monolithic whole.

The turbine exhaust case can have an outer shroud, an inner shroud internal to the outer shroud, an annular exhaust path between the outer shroud and the inner shroud, and a plurality of struts each having a length extending across the annular exhaust path from a radially inner end to a radially outer end, the struts circumferentially interspaced from one another, the struts each having a leading edge and a trailing edge, a stiff connection between the radially inner end and the inner shroud, and a point connection between the radially outer end and the outer shroud.

An apparatus for disassembling and assembling a lower vane carrier and a method for disassembling and assembling the lower vane carrier by using the apparatus are proposed. The apparatus includes a rolling jig that is mounted on the lower vane carrier mounted inside a lower turbine casing, a bolt member that passes through a region where the rolling jig and the lower vane carrier are in contact with each other, and a block member mounted adjacent to the bolt member and configured to prevent the bolt member from being separated.

The invention relates to a guide vane ring for a turbomachine comprising at least one guide vane, at least one bearing body, and at least two inner ring segments. The guide vane has a bearing journal that is arranged in a in form-fitting manner in a bearing bush of the at least one bearing body. The at least two inner ring segments have on their respective outer radial faces a guide channel running along a circumferential direction of the guide vane ring for receiving the bearing body, into which project at least two opposite-lying guide projections of the inner ring segments, said projections running along the circumferential direction of the guide vane ring. The bearing bodyis arranged in the guide channel of the inner ring segments, and the at least two guide projections of the inner ring segments engage in at least two guide grooves of the bearing body.

In one exemplary embodiment, a flow path component assembly includes a support structure having an axial portion and a radial portion and an outer portion arranged between the support structure. The outer portion defines a gap between the outer portion and the axial portion of the support structure. A flange is positioned relative to the gap.

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.

Methods, apparatus, systems and articles of manufacture are disclosed. A split shroud for an inner shroud of a gas turbine engine includes: at least one forward shroud segment and at least one aft shroud segment to couple to the at least one forward shroud segment, the at least one forward shroud segment and the at least one aft shroud segment forming a split line.

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 including a plurality of radial struts rigidly connected to the fan case, and to the core engine. 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.