A mount according to an example of the present disclosure includes a locating pin, a load pin, a fastener, the fastener configured to retain a component on at least one of the locating pin and the load pin, the fastener including a bolt, a mounting boss and a spring, the spring allowing the mounting boss to move with respect to the bolt, and wherein the bolt is held captive in the mounting boss with a captive feature. A gas turbine engine and a method of mounting a component are also disclosed.

A variable flow rate valve mechanism includes a valve, a lock member, a valve attachment member and a spring washer. The valve includes a valve body and a valve shaft. The lock member is fixed to the valve shaft. The valve attachment member is attached to the valve shaft. The spring washer is disposed adjacent the valve attachment member. The spring washer is formed into an annular shape around an axis of the spring washer. The spring washer includes a support portion, a deformable portion and a protrusion portion. The support portion includes a seat surface and an open surface. The deformable portion is connected to the support portion and extends in an inclined manner. The deformable portion includes a contact surface and an opposite surface. The protrusion portion protrudes from at least one of the open surface of the support portion and the opposite surface of the deformable portion.

A vane assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart radially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends radially between and interconnects the outer platform and the inner platform.

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.

A method and system for aligning a component within a turbine casing, and a related turbine casing. In a top-on position, a location of an optical target and another, vertically spaced optical target on the joint flange are measured. After removing at least the upper casing, the optical targets' locations are measured again, and the locations of a pair of reference points on an upper surface of the horizontal joint flange are measured. A prediction offset value is calculated for the component support position in the top-on position based on the locations. The prediction offset value may include a vertical adjustment based, in part, on a translation of a triangular spatial relationship of a number of the reference points and/or a tilt angle, a horizontal adjustment, and a horizontal joint flange surface distortion adjustment. Support position is adjusted by the prediction offset value to improve alignment.

Turbine (1) comprising a casing, an outer metal shroud (9), an inner metal shroud (5) and an annular distributor (2) having a plurality of CMC ring sectors (20), each sector comprising a mast (6), an inner platform (24), an outer platform (26) and at least one blade (28) having a hollow profile that defines an inner housing (280), the inner and outer platforms each having an opening (245, 265) communicating with said inner housing, and the mast (6) passing through said openings and the inner housing and being secured to said casing and connected to said annular sector. Each blade comprises at least one first radial shoulder (72) projecting axially towards the inside of the blade, and each mast comprises at least one second shoulder (71) projecting axially towards the outside of the mast (6) configured to radially cooperate with a first shoulder (72) and radially press the blade (28) against the mast (6).

An assembly for a turbomachine turbine includes at least one ring sector made of CMC material and a support casing including an upstream flange and a downstream flange between which each ring sector is disposed, each ring sector including a base that has a radially external face from which radially extend two lugs, the lugs of each ring sector being retained between the two flanges of the support casing by axial pins each engaged in one of the flanges of the ring support casing and in the lug of the ring sector facing said flange, the assembly further including, for each ring sector, at least one radial retaining pin screwed into the support casing and coming to radially bear against a lug of the at least one ring sector to retain it in position, and anti-rotation system for rotationally locking the radial retaining pin.

A gas turbine component, in particular a stator vane cluster (10), having at least one radial flange (12, 13) with a radial slot (20) for spoke-type centering of a gas turbine element, in particular an inner ring (100), the radial slot (20) having a first slot flank (21), a slot base (23) adjoining the same, and a second slot flank (22) adjoining the same, the slot base (23) being asymmetric with respect to a mid-plane (M) which extends radially and perpendicularly to the circumferential direction and centrally between the two slot flanks (21, 22).

A furnace blower assembly includes a blower housing a blower and a motor. The blower is positioned within the housing and is adapted to rotate relative to the housing. The motor is coupled to the blower. The housing defines an outlet having an external periphery and an internal periphery. The external periphery or the internal periphery of the outlet is adapted to be fitted to a portion of the external periphery or the internal periphery of the duct. The outlet defines a longitudinal axis. The outlet has a peripheral edge and a protrusion extending outwardly from the external periphery or the internal periphery of the outlet. The protrusion is spaced from the peripheral edge of the outlet and is adapted to abut the peripheral edge of the duct.

A gas turbine module includes a gas turbine that has a gas turbine rotor and a turbine shell; an inlet plenum that is connected to an inlet of the gas turbine; an exhaust plenum that is connected to an exhaust of the gas turbine; an enclosure that covers the gas turbine; and a common base on which the gas turbine, the inlet plenum, the exhaust plenum, and the enclosure are mounted. When moving the gas turbine, the gas turbine module is moved together.