A gas turbine engine having an improved air delivery system that includes features for pressurizing and/or cooling various components of the engine while minimizing the impact to the cycle efficiency of the engine, reducing the weight of the engine, and reducing the specific fuel consumption of the engine is provided.

A bearing compartment seal for a gas turbine engine includes at least one seal ring defining an axis and having a radially inward facing sealing surface and a seal runner having a support constructed of a first material and an interface portion constructed of a second material. The interface portion includes a radially outward facing surface. A first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.

Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.

A support assembly for a turbocharger defining a system axis, the support assembly comprising a housing assembly and a bearing assembly. The housing assembly comprises a housing defining at least one support groove and a seal plate. The bearing assembly comprises an outer sleeve defining at least one support tab. The at least one support tab is sized and dimensioned such that, when the outer sleeve is supported by the housing member in a desired orientation, the support tab is within the support groove such that movement of the outer sleeve along the system axis relative to the housing member is inhibited. The seal plate may be configured to define at least one anti-rotation projection arranged relative to the support tab to inhibit rotation of the outer sleeve about the system axis relative to the housing member.

An apparatus has a first member, a shaft rotatable relative to the first member about an axis, and a seal system. The seal system has: a seal carried by the first member and having a seal face; and a seat carried by the shaft and having a seat face in sliding sealing engagement with the seal face. The seal system is a dry face seal system. The seat further includes a section having: an outer diameter surface encircled by the seal; and a rim.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotatable shaft and a cover substantially covering an end of the rotatable shaft. The cover includes a passageway fluidly coupled from outside the shaft to inside the shaft. The cover further includes a fin configured to prevent oil from entering the passageway.

Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: —a rolling bearing (8), —a body (5) for distributing oil, which body is configured to be mounted on a turbine engine shaft (4), said body comprising: i) a first outer cylindrical surface (5a) for mounting the inner ring (12) of the bearing, ii) a ring-shaped scoop (11) for recovering oil, iii) a ring-shaped track (26) of a dynamic seal (22), iv) a circuit (7) for lubricating the bearing and cooling the track, said circuit being formed in the body, characterised in that the ring-shaped scoop is the first scoop (11a) which supplies a first portion (7x) of the circuit with a view to cooling the track, and in that the body comprises a second ring-shaped scoop (11b) for recovering oil, which scoop supplies a second portion (7y) of the circuit with a view to lubricating the bearing.

An assembly is provided for rotational equipment. This assembly includes a seal land and a seal element. The seal land extends circumferentially around and is rotatable about an axial centerline. The seal land includes a seal land surface. The seal element extends circumferentially around the axial centerline. The seal element includes a seal element surface and a seal element passage. The seal element surface is abutted against and is sealingly engaged with the seal land surface. The seal element passage extends through the seal element to an interface between the seal element surface and the seal land surface.

A seal system for a gas turbine engine includes a seal runner manufactured of a Molybdenum alloy material that provides a first coefficient of thermal expansion and a seal ring manufactured of a graphitic material that provides a second coefficient of thermal expansion greater than the first coefficient of thermal expansion.

A bearing is mounted to a static structure outwardly of the shaft, and supporting the shaft. A bearing compartment is defined by face seal arrangements on each of two axial sides of a bearing. Each face seal arrangement includes a seal seat rotating with the shaft and a non-rotating sealing ring. The seal housing is exposed to high pressure air outward of the bearing compartment. A coil spring biases the seal housing towards the seal seat, such that the sealing face is biased into contact with the seal seat by a bias force including a net fluid force acting on the seal housing and the coil spring. The sealing face is defined by a contact portion contacting the seal seat and a feed portion recessed from the seal seat. The feed portion includes a plurality of circumferentially spaced feed slots fluidly connected to at least one annular groove.