A seal assembly includes a rotatable shaft and a stationary housing circumscribing the shaft to form radially inner and radially outer boundaries of a seal cavity and a buffer cavity adjacent to the seal cavity. A retention member engaging the housing within the seal cavity includes an end plate extending radially at the axial boundary between the seal and buffer cavities and a protrusion extending from the end plate into the buffer cavity.

Disclosed is a fairing element intended to be placed in a passage for flow of a fluid, in order to surround an obstacle which crosses the passage so that the fairing element guides the flow of the fluid on two opposite sides of the obstacle. The fairing element is designed such that the pressure of the flowing fluid is constant or approximately constant in an upstream part of the suction surface of the fairing element. A fairing element of this kind can be incorporated into a stator of a turbomachine, in particular of an aircraft turbomachine.

A gas turbine engine component includes an exterior pressure side with a plurality of cooling holes located in the exterior pressure side. A relief cut surrounds at least one of the plurality of cooling holes.

A turbine engine assembly including an air flow guide assembly, including at least one guide vane and at least one structural arm, the vane and arm extending radially about an axis. The arm includes an upstream end portion having a guide vane profile and including a leading edge aligned with that of the vane; a downstream portion; and an intermediate portion including an upper surface extending between an upstream end point and a downstream end point. The upstream end point is separated from the leading edge of the arm by an axial distance of between 0.2c and 0.5c, c being the length of the axial chord of the vane, and the angle of the tangent to the upper surface at the upstream end point is equal to that at the downstream end point ±1 degree.

A nosecone assembly having an axially extending centerline is provided. The assembly includes a nosecone body and at least one access panel. The nosecone body has at least one wall that defines an interior cavity. The wall has an interior surface contiguous with the interior cavity, and at least one window aperture extending through the wall. The access panel has first and second face surfaces. The access panel is attached to the wall interior surface within an attachment region that includes first and second attachment region portions partially contiguous with one another. The first and second attachment region portions define an interior unattached region, and the interior unattached region is aligned with the window aperture.

A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.

A turbulent air reducer assembly for a gas turbine engine includes a windage cover attached to a first standoff and a second standoff, the windage cover tuned to a particular vibration response. A method of managing air within a turbine of a gas turbine engine includes reducing turbulence from a multiple of recesses within a tangential on-board injector with a turbulent air reducer assembly within each of the multiple of recesses, the turbulent air reducer assembly tuned to a particular vibration response from a turbine rotor.

A component is provided for an aircraft. This aircraft component includes an object and a multi-layer coating. The object includes an object surface. The multi-layer coating includes a barrier layer and a laminar flow layer. The covers at least a portion of the object surface. The barrier layer a fluoropolyether, a silicon rubber and/or a polyurethane. The laminar flow layer covers the barrier layer and forms an exterior surface of the component. The laminar flow layer includes a sol-gel siloxane, a rare-earth oxide and/or a phosphate.

A turbine section for a gas turbine engine includes an independently controllable wheel downstream of the first static vane structure and a turbine rotor downstream of the independently controllable wheel. A method of generating thrust for a gas turbine engine, includes rotating a independently controllable wheel located downstream of a combustor and upstream of a turbine rotor to augment a swirl of a core flow combustion gases.

A heat exchanger designed to be fixed to a turbomachine wall delimiting a gas flow stream, this exchanger including a body with a front face through which the gas flow passes; an attachment face to the wall; an external face opposite the attachment face and connected to the front face; two lateral faces connected to the front face; a cover surrounding the front face and extending along the prolongation of the external face and the lateral faces, to delimit an intake with an area smaller than the area of the front face, this intake being located upstream from the front face relative to the gas flow stream.