A fuel system includes a fuel passage for conveying a hydrocarbon fuel. The hydrocarbon fuel is reactive with oxygen to form carbonaceous deposit. A device is disposed in the fuel passage such as to be exposed to the hydrocarbon fuel. The device includes first and second surfaces that are spaced from each other by a clearance gap into which the hydrocarbon fuel can infiltrate. The first and second surfaces are in sliding motion with respect to each other when the device is in operation. A frangible fluoropolymer coating is disposed on at least one of the first or second surfaces along the clearance gap. The coating is subject to the carbonaceous deposit adhering thereon. The coating is configured to allow portions to release by shearing off with the carbonaceous deposit under stress from the sliding motion to uncover a newly exposed face of the coating.

A blocker door assembly for use in a gas turbine engine includes a facesheet including a plurality of openings to facilitate noise attenuation and a body portion coupled to the facesheet. The body portion includes a backsheet integrally formed with a honeycomb core, wherein the body portion is molded from a thermoplastic material.

A blocker door assembly for use in a gas turbine includes a panel, a core integrally formed with the panel, and a plurality of mounting structures extending from at least one of the panel and the core. The plurality of mounting structures are integrally formed with the core and the panel such that the panel, the core, and the mounting structures are co-molded from a thermoplastic material.

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.

A turbomachinery gasket comprising at least a first curved elongated element having a coupling part configured to cooperate with a tubular assembly in order to keep the gasket in position on the tubular assembly, and an outer surface configured to seal against an outer casing provided to house the tubular assembly, the first curved elongated element comprising a first and a second free end, the first free end providing a first protruding lip and the second free end providing a second protruding lip, the first protruding lip being configured to overlap with the second protruding lip of the first curved elongated element or with a second protruding lip of a second elongated element functionally identical to the first one, so that, when the gasket is in use, a seal in that part of the gasket having said protruding lips is granted.

A fan motor includes: a motor housing; a rotating shaft; a rotor; a stator disposed outside the rotor; an impeller having at least one blade and a hub; and an impeller cover surrounding an outer circumference of the impeller and defining an air suction inlet. The impeller cover includes: a shroud having an inner diameter that expands in an air flow direction; and a non-metallic coating layer coated on an inner circumferential surface of the shroud and having a lower strength than the blade. The non-metallic coating layer includes: a first area having a first thickness; a second area having a second thickness thinner than the first thickness and defining a stepped portion with the first area, thereby minimizing leakage flow caused by the pressure difference from a pressure-side surface to a suction-side surface of the blade to reduce flow path loss and improving efficiency of the fan motor.

A method of applying a wear-resistant coating to aluminum sliding contact wear surfaces is disclosed. The method includes providing a plurality of parts having sliding contact wear surfaces and thermal spray coating at least one of a composite aluminum oxide and PTFE or a blend of aluminum oxide and PTFE. The disclosed method may be used to repair aluminum parts subject to sliding contact wear as well as in the design of new aluminum parts subject to sliding contact wear. Improved compressor bleed valves for gas turbine engines and improved fan exit case assemblies are also disclosed.

This impeller cover is provided with: a machinable abradable seal section which has a shroud surface, which faces the outer peripheral surface of an impeller rotating about its axis, and which provides a seal between the outer peripheral surface and the shroud surface; a cover body which covers the impeller from the outside and which has a seal housing section for housing the abradable seal section therein; and a filling material which is interposed between the abradable seal section and the cover body. The seal housing section has a fitting inner peripheral surface which is extended along the axis in order for the outer peripheral surface of the abradable seal section to fit thereto, a reference surface which is used for axial positioning of the abradable seal section by being brought into contact with the abradable seal section from one side in an axial direction, and a capturing part which forms a gap in at least at a part of the section between the abradable seal section and the seal housing section in order to capture any excess filling material.

A compressor assembly may include a compressor housing and a compressor impeller disposed within the compressor housing. The compressor housing may have an internal aerodynamic surface that defines a circumferentially extending volute, and the compressor impeller may have an external aerodynamic surface that faces toward at least a portion of the internal aerodynamic surface of the compressor housing. A nonstick coating may be formed on the internal aerodynamic surface of the compressor housing or on the external aerodynamic surface of the compressor impeller. The nonstick coating may prevent foreign material introduced into the compressor assembly from collecting on the internal aerodynamic surface of the compressor housing or on the external aerodynamic surface of the compressor impeller.

An aerofoil blade having a root portion provided with a low friction coating layer. The low friction coating layer is affixed to the root portion by an adhesive layer. The adhesive layer has a service temperature of 125 C. or more, for example 140 C. or more.