The present application discloses a diffuser system and a centrifugal compressor comprising the same. The diffuser system comprises: a passage through which a compressed gas is flowable; and a wall defining the passage, the wall comprising a movable part which is driven to enter the passage so as to change a flow area of the passage, wherein the movable part comprises an elastomer configured to expand to guide the flow of the compressed gas when at least a portion of the movable part enters the passage, and to retract when the movable part withdraws from the passage. The diffuser system involved in the present application re-orients a flow route of the compressed gas in the passage.

A method for manufacturing a stage of a steam turbine comprising the steps of milling a block of material to define a sector having a plurality of blades, each blade having an external surface; machining an opening in the external surface of at least one of the blades; machining a cavity in fluid communication with the opening; the step of machining the cavity being performed by wire electric discharge machining.

A hybrid grommet assembly for a vane comprising a body portion comprising a first lip opposite a second lip forming a slot receiver, said slot receiver configured to receive a shroud slot of a shroud; said body portion comprising a vane receiver extending from said body portion and configured to receive a vane; a fiber integral within said body portion; and a potting coupled to said grommet proximate said vane receiver, wherein said potting fills a gap between the grommet and the vane.

The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.

Multistage centrifugal compressor provided with a shaft with blades, which is mounted in a housing with bearings. At least one bearing is provided with a bearing damper element including a ring arranged between the shaft and the bearing. The ring includes slots through the thickness of the ring in the axial direction (X-X′) and at a distance from the radially-directed inner and outer surface of the ring. The slots are at least partially overlapping, and: A) the slots are filled with a liquid, and the axial annular surfaces are closed off by means of a protective cap; or: B) at least one of the annular surfaces is provided with a viscoelastic material or hysteretic damping material sandwiched between two concentric discs, which discs are attached to the ring; or: C) the slots are filled with a viscoelastic material.

An apparatus is provided for an aircraft propulsion system. This apparatus includes a variable area nozzle apparatus. The variable area nozzle apparatus includes a plurality of panels, a plurality of inter-panel members and an actuation system. The panels are arranged circumferentially about an axial centerline. The panels include a first panel and a second panel. The inter-panel members are arranged circumferentially about the axial centerline. The inter-panel members include a first inter-panel member between and connected to the first panel and the second panel. The first inter-panel member is configured from or otherwise includes an elastomeric material. The actuation system is configured to move the panels and the inter-panel members between a restricted flow arrangement and an unrestricted flow arrangement. The actuation system includes a first linkage and a second linkage. The first linkage is coupled to the first panel. The second linkage is coupled to the second panel.

In an embodiment, a ducted fan assembly includes a housing that further includes a rotor. The ducted fan assembly also includes a rim that extends around at least a portion of a perimeter of the ducted fan assembly, where the rim defines an opening surrounding at least a portion of the housing. The ducted fan assembly also includes a skin that is attached to the rim and extends around the at least a portion of the perimeter of the ducted fan assembly to form a leading edge of the ducted fan assembly, the skin and the rim creating a cavity therebetween. The cavity is at least partially filled with a material to absorb energy from an impact of the skin with a foreign object.

A turbine engine blade having an aerodynamic surface extending a first direction between a leading edge and a trailing edge and in a second direction, perpendicular to the first direction, between a root of the blade and a tip of the blade, the aerodynamic surface being made of a fiber-reinforced organic matrix composite material, and a metallic structural reinforcement bonded by an adhesive joint to the leading edge whose shape it follows and which has over its entire height a substantially V-shaped section with a base extended by two lateral flanks having a thinned profile at free ends directed toward the trailing edge, the adhesive joint being locally supplemented below the free ends of the lateral flanks by an elastomeric polymer introduced in the form of solid particles into the adhesive joint and adhered to the aerodynamic surface and/or the free ends of the lateral flanks during a polymerization phase.

A heat insulating sheet member capable of enhancing a heat insulating performance of an exhaust gas introduction path by an easy operation, including such a path in a turbocharger. The heat insulating sheet member is a bendable member formed from an inorganic flexible material. The heat insulating sheet member includes a first region corresponding to an inlet of a bottom wall portion, a second region corresponding to at least a terminating end portion of the scroll portion, a third region provided between the first region and the second region and corresponding to a coupling wall portion, and a fourth region corresponding to an outer peripheral wall portion. The first region and the third region, the third region and the second region, and the first region and the fourth region are coupled to each other with the inorganic flexible material in a continuous state.

The disclosure describes composite nosecones and techniques for forming composite nosecones including a matrix material, relatively higher-modulus reinforcement elements, and relatively tougher polymer-based reinforcement elements. An example composite nosecone includes a body substantially symmetrical around a central axis. The body includes a side wall defining a diameter of the body that increases from a forward side of the body to an aft side of the body. The body includes a composite material including a plurality of relatively higher-modulus reinforcement elements, a plurality of relatively tougher polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively higher-modulus reinforcement elements and the plurality of relatively tougher polymer-based reinforcement elements. The plurality of relatively higher-modulus reinforcement elements are different from the plurality of relatively tougher polymer-based reinforcement elements.