Abstract: The de-aerator can be used to separate air from oil in an aircraft engine lubrication system. The de-aerator can include a swirler cavity extending circumferentially around axis and axially between a proximal wall and a distal wall, a separation path dividing within the swirler cavity into a radially outer oil segment leading to an oil outlet and a radially inner air segment leading to an air outlet, and a swirling conduit portion having a length turning around the axis upstream of an opening in the proximal wall along the separation path.

Abstract: A compressed air conduit can have a cross-sectional area, and a valve, the valve having at least one arm being deployable laterally into the cross-sectional area of the conduit to restrict flow within the conduit.

Abstract: A three-dimensional structure is obtained from a tubular preform, which is obtained from a net of the Chebyshev type having a flared shape maintained by hoops, spacers, or cables. A method for installing such a structure, in which method the tubular preform is brought to the installation point, then deformations are applied to the preform that allow the final desired flared shape to be achieved.

Abstract: A compressed air conduit can have a cross-sectional area, and a valve, the valve having at least one arm being deployable laterally into the cross-sectional area of the conduit to restrict flow within the conduit.

Abstract: A seal runner for a gas turbine engine, the seal runner including an annular body having a sealed cavity defined therein, the cavity being elongated along an axial direction of the body and being annular, the cavity at least partially filled with a coolant, the coolant being liquid across a range of operating temperatures of the gas turbine engine, the coolant having a temperature dependent density across the range of operating temperatures of the gas turbine engine. A gas turbine engine and a method of cooling a seal runner exposed to a temperature gradient are also discussed.

Abstract: A seal runner for a gas turbine engine, the seal runner including an annular body having a sealed cavity defined therein, the cavity being elongated along an axial direction of the body and being annular, the cavity at least partially filled with a coolant, the coolant being liquid across a range of operating temperatures of the gas turbine engine, the coolant having a temperature dependent density across the range of operating temperatures of the gas turbine engine. A gas turbine engine and a method of cooling a seal runner exposed to a temperature gradient are also discussed.

Abstract: An anti-vortex device for use in a compressor rotor assembly of a gas turbine engine is described. Spaced-apart radial passageways extend from an axially extending passage provided in a central area of the device to an outer peripheral rim surface thereof. The radial passageways channel air from the primary gaspath about the rotor assembly to the axially extending passage where the air is directed into a central axial passage of the rotor assembly.

Abstract: An anti-vortex device for use in a compressor rotor assembly of a gas turbine engine is described. Spaced-apart radial passageways extend from an axially extending passage provided in a central area of the device to an outer peripheral rim surface thereof. The radial passageways channel air from the primary gaspath about the rotor assembly to the axially extending passage where the air is directed into a central axial passage of the rotor assembly.