A washer includes a first lobe comprising a first hole, a second lobe comprising a second hole, a third lobe comprising a third hole, and a fourth lobe comprising a fourth hole. A first leg extends from the first lobe to the second lobe, and a second leg extends between the third lobe and the fourth lobe, wherein the second leg is parallel to the first leg. A third leg extends from the first lobe to the third lobe and spaces the first leg from the second leg such that the second lobe is disposed opposite the fourth lobe.

A bearing ring with integrated cooling channels and a method for producing a bearing ring with integrated cooling channels are provided.

A damper system may include an inner damper having a first annular geometry and a textured surface. An outer damper may also have an annular geometry and be disposed about the inner damper. The outer damper may have a textured surface. The textured surfaces of the inner damper and outer damper may define a cavity that is configured to contain a viscous fluid.

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.

A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case. At least one spoke is attached to the inner frame case. A passage extends through at least one spoke, the inner frame case, and the bearing support member.

A cooling device for an internal combustion engine including: an ebullient cooling system in which a refrigerant cools the internal combustion engine by boiling in the internal combustion engine, and a rankine cycle system including a superheater that superheats the refrigerant discharged from the internal combustion engine, a turbine to which the refrigerant discharged from the superheat is supplied, and a condenser that condenses the refrigerant discharged from the turbine; wherein the rankine cycle system includes a supply path that supplies a liquid-phase refrigerant discharged from the condenser to a shaft part of the turbine, and a first supply part of the condenser to which the refrigerant discharged from the turbine is supplied is arranged higher than the shaft part of the turbine in a gravity direction.

A bearing system for a turbocharger rotor assembly that includes an elongated bearing carrier with anti-friction bearings on each end carried in a stationary housing. The elongated bearing carrier is supported within the housing by axially spaced elastomeric bands in grooves in the outside diameter of the bearing carrier that cooperate with grooves in the bore of the stationary housing within which the elastomeric bands are seated to carry the axial thrust of the rotor assembly in both axial directions.

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotatable shaft defining a longitudinal axis, and a bearing housing extending along the longitudinal axis to define a bearing compartment. The bearing housing has a first seal land defined along an inner diameter of the bearing housing, a seal carrier fixedly attached to an outer periphery of the shaft, and a seal member extending outwardly from the seal carrier. The seal member defines a plurality of helical grooves facing radially outward to establish a first sealing relationship with the first seal land, and each one of the helical grooves has a major component extending in an axial direction relative to the longitudinal axis. A method of sealing for a gas turbine engine is also disclosed.

A gas turbine arrangement, including a gas generator section (A), a power turbine section (B), and a generator section (C) coupled on a common shaft (10). The power turbine has its bearing block (12) provided with a copper cooling cup (9), which possesses a high thermal conductivity and conveys heat flux away from the side and block of the bearing and which has a design that enables the effect of a penetrating airflow.

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.