A method is provided for preventing oil escape into an exhaust gas during operation of a turbocharged engine. The method includes providing pressurized fluid to an area sealing off a bearing housing of an axial turbine unit from an adjacent exhaust conduit downstream of the axial turbine unit, and detecting a malfunction in the provision of pressurized fluid. Further to this, the method includes the step of, in response to such malfunction detection, controlling an exhaust pressure increasing device arranged downstream of the axial turbine unit for increasing the pressure inside the exhaust conduit upstream of the exhaust pressure increasing device.

Oil slinger systems include a seal runner comprising an annular radial member having a radius (R) and an outer axially extending member having an axial length (L), wherein a proximal surface of the outer axially extending member comprising a plurality of helical grooves. Methods of radial convective cooling include pumping a cooling liquid through the oil slinger system and convectively cooling the oil slinger.

A seal system has: a first member; a seal carried by the first member and having a seal face; and a second member rotatable relative to the first member about an axis. The second member has: a seat on a first piece of the second member, the seat having a seat face in sliding sealing engagement with the seal face; and a radially outwardly closed collection channel for collecting centrifuged oil; a second piece encircling and attached to the first piece and having a circumferential array of apertures; and cooperating with the first piece to define a plenum; and a flowpath from the collection channel passing radially outward axially spaced from the seat face to cool the seat face and passing axially away from the seat face in the plenum.

There is described an oil contamination detection system and method. The system comprises a forward sensor package, a rearward sensor package, a catalytic chamber, and a computing device. The method comprises obtaining sensor measurements from the forward sensor package and the rearward sensor package, and detecting the presence of oil in the air flow from the sensor measurements.

A seal arrangement for a gas turbine engine includes a seal runner having a sealing lip extending radially outwardly from a root portion to a tip portion. A static seal is mounted in axially opposed facing relationship to the sealing lip. The static seal and the sealing lip define an axial gap therebetween. A point of flexion is provided in the root portion to allow the sealing lip to flex relative to the axial gap under centrifugal loads, and wherein a center of gravity of the sealing lip is disposed radially outwardly from the point of flexion by a first predetermined amount and axially offset from the point of flexion by a second predetermined amount. The first and second predetermined amounts are selected to modulate the centrifugal flexion of the sealing lip so as to compensate at least partially for thermally induced deformation of the sealing lip.

A sump housing apparatus for a gas turbine engine includes: an annular body; and a plurality of service tubes arrayed around the body, each service tube having a proximal end intersecting the body and an opposed distal end, each service tube having an inner port communicating with an interior of the body; wherein the body and at least one of the service tubes are part of a monolithic whole.

An exhaust-gas turbocharger (1) with a bearing housing (2), a shaft (5) mounted in the bearing housing (2), a turbine wheel (6) which is arranged on the shaft (5), a compressor wheel (7) which is arranged on the shaft (5), and a wheel side space (10) between a rear wall (8) of the turbine wheel (6) or compressor wheel (7) and an outer surface (11), which faces toward the rear wall (8) of the bearing housing (2). In the outer surface (11) of the bearing housing (5), there is formed at least one groove (13, 18) for disrupting the flow generated by the rotating rear wall (8).

A floating brush seal assembly includes a ring-shaped housing defining a radially inwardly open internal cavity; a brush seal in the cavity and having bristles extending radially inwardly and offset to seal against a rotating body; a radial spring positioned to exert a radial inwardly directed force against the brush seal relative to the housing; and an axial spring positioned to exert an axially directed force against the brush seal relative to the housing.

Aspects of the disclosure are directed to a system associated with an engine of an aircraft. The system includes a shaft configured with at least one axially-oriented hole, and an oil scoop configured to receive oil and provide the oil to the shaft, wherein the oil scoop is manufactured independently from the shaft, and wherein the oil scoop includes at least one retention mechanism for coupling to the shaft after the at least one axially-oriented hole is created in the shaft.

A seal assembly for a gas turbine engine, may be manufactured in two pieces, the first piece is a seal plate with a cavity around its inner wall and the second piece is a sleeve that mounts in the cavity of the seal plate. The sleeve may have oil distribution channels that deliver oil to subsequent components and apertures that deliver oil to the seal plate. The volume of oil delivered to the seal plate can be set by the number of apertures and related radial holes in the sleeve. Because the sleeve delivers oil through the apertures and radial holes to an annulus in the cavity of the seal plate, cooling bores in the seal plate need only be drilled into the annulus and the number of cooling bores can be independent of the number of radial holes in the sleeve.