A bearing assembly is provided. The bearing assembly includes an inner race configured to couple to a shaft, an outer race disposed around the inner race, and a housing disposed around the outer race. The housing and the outer race define an annulus and a buffer region, and the buffer region defines an axial boundary of the annulus.

A sealing arrangement has a turbine static structure with contact surfaces, a bearing compartment with contact surfaces, and a cavity between the turbine static structure and the bearing compartment. There are also two seals, wherein each seal is configured to contact the turbine static structure and the bearing compartment.

The invention relates to an exhaust gas turbocharger having a hydrodynamic plain bearing or a hydrodynamic plain bearing, comprising a rotor (10) and a counter-bearing part (50) assigned to the rotor (10), wherein a rotor bearing surface of the rotor (10) and a counterface of the counter-bearing part (50) face each other to form the hydrodynamic plain bearing in the form of a combined journalthrust bearing, having a continuous hydrodynamically load bearing gap formed between the rotor bearing surface and the counterface, wherein the rotor bearing surface and/or the counterface, when cut longitudinally and through the axis of rotation (R) in sectional view, form(s) a bearing contour forming merging contour sections (17.1 to 17.3; 44.1 to 44.3; 53.1 to 53.3) to generate hydrodynamic load capacities in both the radial and the axial direction, wherein a contour section (17.3; 44.3; 53.3) in sectional view in a first bearing area forms a linear section that is part of a, in particular cylindrical or partially cylindrical, bearing section rotating at least sectionally about the axis of rotation (R), wherein a further contour section (17.1; 44.1; 53.1), in sectional view in a second bearing area, forms a further linear section, which is part of a further bearing area rotating at least sectionally about the axis of rotation (R), wherein this further linear section forms an angle with the axis of rotation (R), and wherein the first and the second bearing area merge via a transition section. According to the invention, a friction-optimized bearing system is to be created, which is easy to manufacture and ensures a reliable and effective bearing arrangement even under highly dynamic loads. According to the invention, this is achieved by the further linear section forming an angle in the range from >30? to <90? with the axis of rotation (R).

A regenerative gas turbine combustor is provided that enable to reduce an amount of leakage of compressed air before preheating to compressed air after the preheating. The regenerative gas turbine combustor is such that a compressed air passage between a combustor inner cylinder 10 and a tail cylinder 12, and a combustor outer cylinder 7 is blocked by a division wall 15 at a position between a bleeding port 13 and an injection port 14, and compressed air is preheated in a regenerator 4 and then the compressed air thus preheated is burnt together with fuel. This combustor includes seal rings 17a-17c, a holder 16 installed on the inner circumferential portion of the division wall 15 and having ring grooves 25a-25c for holding the respective seal rings 17a-17c, and gaps 20 provided between the inner circumferential surfaces of the ring grooves 25a-25c and the outer circumferential surfaces of the seal rings 17a-17c.

A system is provided associated with an engine of an aircraft. The system includes a ring, a runner and at least one radially-oriented hole associated with the runner that is configured to supply oil to an interface between the runner and the ring. The at least one hole is contained within an axial projection of the ring.

A turbocharger includes: a turbine wheel; a turbine housing; a bearing housing; a shroud having a facing surface which faces a tip of a blade of the turbine wheel and being configured to surround the turbine wheel, the shroud comprising a separate member from the turbine housing and being disposed inside the turbine housing via a gap with respect to the turbine housing; a mount supported to at least one of the turbine housing or the bearing housing, at a position closer to the bearing housing than a scroll flow path in an axial direction of the turbine wheel; and at least one connection part connecting the mount and the shroud.

A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller and a shroud covering a bladed portion of the centrifugal impeller. The compressor assembly includes a diffuser that is attached to the shroud via a pair of flanges, the diffuser including a strut that is mounted through an aft-extending leg to a base of an intercase. A sealing assembly is attached to the diffuser and is attachable to a transition duct that is positioned to receive air from the diffuser. The sealing assembly is configured to prevent air from passing through the sealing assembly while allowing relative motion to occur between the transition duct and the diffuser.

An annular seal flange is formed at an inner peripheral edge portion of an upstream-side seal ring. The seal flange projects in a downstream direction. When seal rings are viewed from radially inside, the seal flange of the upstream-side seal ring is designed to at least partially occlude an end gap of the downstream-side (the most downstream-side) seal ring.

This shaft sealing device comprises: a housing that has a storage groove; a seal body stored in the storage groove; and a projected part that projects from one of the housing and the seal body toward the other in the storage groove in an axial direction. The seal body divides an annular space into a high-pressure region on a first side in the axial direction and a low-pressure region on a second side in the axial direction. The housing has a connection part that connects the low-pressure region with the inside of the storage groove. The projected part divides a portion between an opposite surface and a low-pressure-side lateral surface of the seal body into a first space on the radially outer side and a second space on the radially inner side. The connection part connects the first space with the low-pressure region.

A system is provided associated with an engine of an aircraft. The system includes a ring, a runner and at least one radially-oriented hole associated with the runner that is configured to supply oil to an interface between the runner and the ring. The at least one hole is contained within an axial projection of the ring.