Systems and methods for reducing friction during gas turbine engine assembly may comprise, a rear hub which may comprise a conical web, a horizontal arm coupled to the conical web, and/or a hub kickstand coupled to the conical web. The conical web, horizontal arm, and/or hub kickstand may converge at a pivot point. The hub kickstand may be removably coupled to the tie shaft.

In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.

The invention relates to a turbine engine (2) compressor shroud, comprising: first and second sections (130, 230) and respective flanges (131, 231), the flanges (131, 231) making it possible to hold the two sections (130, 230) together, the first section (130) comprising a cylindrical surface (137) forming a seat for an actuating device (136, 140, 166, 168, 170) for orienting stator blades (126), characterised in that the first shroud (130) comprises a tubular wall (132) axially overlapping both flanges (131, 231) and said cylindrical surface (137) is an outer surface of the tubular wall (132). The invention also relates to an assembly with the shroud (130, 230), the blade (126) and means (140) for actuating the orientation of the blade (126), the shroud being produced using the kit described above. The invention finally relates to a method for assembling a compressor with such an assembly.

The present invention provides a splinter shield for a vacuum pump, capable of reducing costs of the splinter shield by obtaining a single sheet of splinter shield having a required strength, in which fastening strength to a fixing groove is enhanced to prevent the splinter shield from bending toward the inside of a pump and coming into contact with equipment inside the pump when air rushes into the pump through an inlet port and to prevent the splinter shield from falling. Furthermore, attachment and removal of the splinter shield with respect to the inlet port are facilitated. The present invention is a splinter shield for a vacuum pump in which a rim formed in a circumferential edge portion of the splinter shield is inserted into a fixing groove that is provided in a concave manner in an inner circumferential portion of an inlet port, and the splinter shield is provided in a tensioned manner to the inlet port by pushing a retaining ring into the fixing groove, wherein locking parts that are locked into the retaining ring at a plurality of sections in the rim are provided in a standing manner at substantially right angles to the rim.

An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face.

A rotor of a multi-staged axial compressor which extends along an axis of rotation. The rotor has a shaft which has rotor blade slots. Rotor blades of the rotor are arranged next to one another in the circumferential direction and are each secured to the rotor blade slots by a blade root to form a respective rotor blade stage. At least two rotor blade stages are provided in axial succession and an interspace slot, extending in the circumferential direction, is provided in the shaft axially between the two rotor blade stages. The rotor blade slots open into the interspace slots and blade roots of the rotor blades are insertable radially into the interspace slots and can be pushed into the rotor blade slots. The rotor has an interspace cover which covers the interspace slots, wherein the interspace cover is designed segmented into interspace cover segments in the circumferential direction.

A method for the manufacture of a blisk drum is described. Disc forging for inertia welding together are provided with sacrificial material whose shape and position is selectively provided such that, on completion of the inertia welding process, integral blades can be fashioned from the sacrificial material. Other components such as buckets and balancing lands may also be provided from the sacrificial material.

A guide vane (10, 10′) according to the invention for a guide vane ring of a turbomachine has a vane element as well as a guide vane plate (12) for its support on an inner ring (20). The guide vane plate has a cover surface (14) facing the vane element, a base surface (17) lying opposite to the cover surface, and an edge surface (15) joining the cover and base surfaces. In a first region (B.sub.1), the edge surface forms a chamfer (16) of the vane plate, and in a second region (B.sub.2), which forms the edge of a sector of the guide vane plate that is different from that of the first region (B.sub.1), the edge surface runs along a cylindrical surface. A method comprises inserting a plurality of guide vanes (10, 10′) according to the invention into respective uptakes (21) in an inner ring (20).

Methods for repairing gas turbine engine casings and repaired casings are provided. In this regard, a representative method for repairing a gas turbine engine casing includes: removing an annular portion of the engine casing; and attaching an annular replacement portion to the engine casing.

A device for guiding variable pitch stator vanes of a turbine engine is provided. The device includes a plurality of inner ring angular sectors arranged end-to-end in order to form an inner ring, each inner ring sector having chimneys passing radially through the inner ring sector, a plurality of cylindrical bushings, each being put into place in a chimney of the inner ring from the inside and each serving to receive a guide pivot of a stator vane, a plurality of reconstitution ring angular sectors arranged end-to-end in order to form a reconstitution ring and put into place radially from the inside against the inner ring, and a plurality of blocking elements passing axially through the inner and reconstitution rings in order to assemble the rings together.