A dovetail root of a fan blade configured for operation within the fan assembly of a gas turbine engine. The dovetail root is imparted with a compressive residual stress layer along the outer faces of the dovetail root preventing crack formation within the dovetail root when the gas turbine engine is in operation. To further protect and structurally enhance the dovetail root, a wear covering is disposed on the dovetail root. The wear covering may consist of a composite laminate layer that is bonded to the metallic core of the dovetail root providing additional cracking protection of the dovetail root when the gas turbine engine is in operation.

A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.

A filter screen includes a plate body with an upstream surface, an opposed downstream surface, and an array of apertures extending between the upstream surface and the downstream surface. A polytetrafluoroethylene-based layer overlays the upstream surface between apertures of the aperture array, the polytetrafluorethylene-based layer being conformally disposed over the upstream surface of the plate body and spanning the upstream surface between the apertures of the aperture array to slow deposition of carbonaceous deposits on the filter screen.

A spool and sleeve assembly for a metering valve comprises a spool body defining a center axis, and a sleeve body having a bore that receives the spool body. The sleeve body includes at least one metering window open to the bore and is moveable between a metering position to control flow through the metering window and a shutoff position where flow is prevented from exiting an outlet end of the bore. A seal assembly reacts between the spool body and the sleeve body to provide at least a first sealing interface and a second sealing interface axially spaced from the first sealing interface when the spool body is in the shutoff position. A metering valve for a fuel system is also disclosed.

Described herein a bucket for use in the last stage of a steam turbine engine. The bucket includes a titanium-based alloy having a leading edge wherein the leading edge includes titania having a plurality of pores and a top sealing layer filling the plurality of pores, the sealing layer selected from the group consisting of: chromium, cobalt, nickel, polyimide, polytetrafluoroethylene and polyester.

An inlet cone for an aircraft turbomachine, having at least one first portion made of a first material, referred to as rigid material, and at least one second portion made of a second material which has a hardness less than that of said first material and which is referred to as flexible material, these second portions being configured to deform elastically in the radial direction with respect to the axis when the cone is being driven to rotate.

The invention proposes a guide arm for guiding at least one element having an elongated shape (20), corresponding to a set of cables and/or pipes. The arm comprises an inner cavity (62) opening on the outside of the arm at each of the ends thereof, and in which the elements having an elongated shape can extend. According to the invention, this structure more particularly comprises: a frame (8) comprising a beam (18) linked to means (30, 36, 44) for holding the elements having an elongated shape on the outside and along the beam, and a cover (54) of which the walls (56, 58) cover the holding means of the frame, and are engaged with the beam, in such a way as to form the inner cavity in which the elements having and elongated shape extend,
shock-absorbing means (68) being arranged between the means (30, 36, 44) for holding the elements having an elongated shape (20), and the longitudinal walls (56, 58), in such a way as to reduce and damp the movements of the means for holding in the cavity (62).

A turbomachine blade is made of composite material formed of woven fibers and embedded in a polymerised resin. The blade includes a root connected by a stilt to a vane which comprises a pressure side and a suction side. At least one anti-wear strip of fabric is located on a surface of the root and/or the stilt. At least one anti-wear strip is secured to the root surface in a unitary manner by the resin.

A power transmission system includes a shaft, a stator disposed within the shaft and substantially concentric with the shaft; and at least one supporting element positioned between the stator and the shaft and configured to support the shaft on the stator to reduce a vibration of the shaft and allow the shaft to rotate relative to the stator. A gas turbine engine including the power transmission system is also described.

A non-collapsible flexible sealing membrane (or bellows) for incorporation in a mechanical seal assembly and use in rotary shaft equipment. The sealing membrane includes a substantially radially outward extending first flange portion, which can be urged into an axially shiftable ring by a biasing mechanism. The sealing membrane further includes a substantially axially outboard extending second coaxial portion, substantially radially inward of the balance diameter of the seal. The horizontal portion is advantageously held fixed to a stub sleeve by an annular band. The angle between the vertical portion and the horizontal portion of sealing membrane enables directional control of the forces acting on stub sleeve and primary ring.