An apparatus and method for protecting an inner radial surface of a radial member of a turbomachine from corrosion are provided. The method may include shaping the inner radial surface of the radial member and a corresponding outer radial surface of a corrosion-resistant liner. The method may also include heating the radial member to increase a diameter of the inner radial surface of the radial member, and inserting at least a portion of the corrosion-resistant liner into the radial member. The method may further include attaching the corrosion-resistant liner to the inner radial surface of the radial member to thereby protect the inner radial surface of the radial member of the turbomachine from corrosion.

One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.

A rotor for a turbomachine includes a rim defining a base of a rotor, an airfoil shaped blade extending from said rim and defining a chord line and a bore extending from said rim opposite said airfoil shaped blade. The rim further includes at least one rail extending away from said airfoil shaped blade.

A method is provided of processing one or more blades of a row of blades which forms part of a rotor for a gas turbine engine. The method includes: providing a rotor disc having a slot for mounting one or more blades; applying tape at one or both sides of the slot such that when the blades are loaded in the slot the tape reduces a range of tilt angles which can be adopted by the blades; loading the blades in the slot; and performing a processing operation on the loaded blades.

A supporting structure for a gas turbine engine comprises an inner ring, an outer ring, and a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings, said radial elements being configured to transfer loads between the inner ring and the outer ring, wherein a gas channel for a primary axial gas flow is defined between the inner and outer rings, wherein the supporting structure has an inlet side for primary gas flow entrance and an outlet side for primary gas outflow, wherein the radial elements have an airfoil shape with a leading edge directed towards the inlet side, a trailing edge directed towards the outlet side, and two opposite sides connecting the leading edge and the trailing edge, and wherein at least a first of said radial elements is connected to an adjacent part of the supporting structure via a weld joint that extends across the leading edge and circumferentially at least partly around the first radial element.

A method of fabricating a composite material casing for a gas turbine engine, the method including making an outer shroud including a platform and a flange, making an inner shroud of smaller diameter than the outer shroud and including a platform and a flange, making a plurality of casing arms, each including a blade that is terminated at each radial end by a respective platform, arranging a plurality of openings in the respective platforms of the shrouds, each opening serving to receive a platform of a casing arm, and assembling the casing arms with the outer shroud and with the inner shroud by inserting the platforms of the casing arms in the openings of the shrouds. A composite material casing is obtained by such a method.

Single-airfoil vanes each having an inner platform, an outer platform, and an airfoil are obtained by three-dimensionally weaving a fiber blank in a single piece, by shaping the fiber blank to obtain a single-piece fiber preform, and by densifying the preform with a matrix to obtain a vane of composite material forming a single piece with inner and outer platforms incorporated therein. A plurality of vanes is assembled together at an intermediate stage of densification to form a multi-airfoil composite material guide vane sector for a turbine nozzle or a compressor diffuser and the assembled-together vanes are bonded together.

A stator element for a Holweck pump stage has a base shape of substantially cylinder jacket shape or a kit of parts for a stator element for a Holweck pump stage which has a base shape of a substantially cylinder jacket shape, wherein the stator element or the kit of parts comprises a plurality of stator parts which are separate from one another, which are assembled to form the stator element or can be assembled to form the stator element. A vacuum pump having a Holweck pump stage as well as to a method of manufacturing a stator element for a Holweck pump stage or of manufacturing a kit of parts for a stator element for a Holweck pump stage are also disclosed.

Various embodiments include approaches for installing a flow sleeve relative to a gas turbine transition piece. Some embodiments include an apparatus for coupling a gas turbine transition piece with a flow sleeve, the installation apparatus having: a radially inner ring; a plurality of expander segments extending radially outward from the radially inner ring, the plurality of expander segments each having an axially ramped segment sized to gradually expand the flow sleeve to couple with the gas turbine transition piece as the flow sleeve is moved along the plurality of expander segments; and a circumferentially disposed space separating each pair of adjacent expander segments in the plurality of expander segments.

Provided is a method of manufacturing a rotary machine, which includes: a casing forming process of forming a casing of the rotary machine that has multiple opening parts and suctions and discharges a fluid; a surface activating process of supplying a pretreatment liquid into the casing, then discharging the pretreatment liquid from the casing through the opening parts, and activating an inner surface of the casing after the casing forming process; a plating process of performing supply and discharge of a plating liquid into and from the easing through the opening parts to circulate the plating liquid and plating the inner surface of the casing after the surface activating process; and an assembling process of providing a rotating body that is rotatable relative to the casing so as to he covered from an outer circumference side by the casing plated in the plating process.