An internal combustion engine, ICE, system, includes a turbocharger having a turbine and a compressor for compressing intake air and feeding the intake air to the ICE. A turbo turbine unit is disposed in an exhaust gas path downstream the turbocharger to receive exhaust gas from the turbocharger. The turbo turbine unit having a turbine wheel, a bearing housing defining an inside volume for containing lubrication oil, and a sealing arrangement positioned in the vicinity of the turbine wheel for preventing lubrication oil from escaping from the inside volume of the bearing housing to an exhaust duct of the turbo turbine unit. A buffer air conduit extends between a selected position at the compressor and a buffer air inlet of the turbo turbine unit. The buffer air inlet is in fluid communication with a buffer air channel inside the turbo turbine unit to direct buffer air to a position in-between axially opposite arranged annular sealing members to provide a counter-pressure against at least one of the annular sealing members.

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.

An exhaust-gas turbocharger (1) with a compressor wheel (2); with a turbine wheel (3); and with a shaft (4) on which the compressor wheel (2) and the turbine wheel (3) are arranged in a rotationally secured manner. The turbine wheel (3) has a through-opening (5) in which a first end region (6) of the shaft (4) is arranged, and the turbine wheel (3) is braced between an end-side stop (7) connected to the end region (6) and a compressor wheel-side shaft sleeve (8) fixed on the shaft (4).

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 dry gas mechanical seal system configured to inhibit the emission of process gas. The mechanical seal system having tandem first and second stage seals, and a single separation gas supply subsystem configured to direct a supply of separation gas from an inlet through interfacing portions of the first stage seal into a process cavity and from the inlet through the interfacing portions of the second stage seal and out through an outlet to the atmosphere, thereby inhibiting the emission of process gas between a compressor housing and a rotating compressor shaft.

An assembly is provided for rotational equipment. This assembly includes a stationary structure, a rotating structure, a seal element and an anti-rotation lock. The rotating structure is rotatable about an axis. The rotating structure is configured as or otherwise includes a seal land. The seal element is configured to seal a gap between the stationary structure and the seal land. The seal element extends circumferentially about the axis. The seal element axially contacts the seal land. The anti-rotation lock projects radially into the stationary structure and the seal element. The anti-rotation lock is configured to at least substantially prevent rotation of the seal element relative to the stationary structure.

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 journal—thrust 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).

The invention relates to an exhaust gas turbocharger having a fluid dynamic bearing having 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 a fluid dynamic bearing, wherein the rotor bearing surface and/or the counterface form(s) a continuous bearing contour when cut longitudinally and through the axis of rotation (R) in sectional view, which bearing contour(s) are formed of at least two contour sections (44.1 to 44.3; 53.1 to 53.3) to generate fluid dynamic load capacities in both the radial and the axial directions, wherein the bearing surface of the rotor (10) is formed by a rotor part (40), which is connected to a rotor shaft (11) and is secured on the rotor shaft (11), and wherein the rotor part (40) is supported relative to the rotor shaft (11) in the area of a support section (14) of the rotor shaft (11). In order to be able to provide such an exhaust gas turbocharger with a compact and efficient bearing arrangement having a fluid dynamic bearing, wherein at the same time the fluid dynamic bearing can be easily mounted using few parts, provision is made according to the invention that the support section (14) and at least one of the contour sections (53.1 to 53.3) of the counter-bearing part (50) at least sectionally overlap in the direction of the axis of rotation (R).

The invention relates to an exhaust gas turbocharger having a fluid dynamic bearing having 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 a fluid dynamic bearing, wherein the rotor bearing surface and/or the counterface form(s) a continuous bearing contour when cut longitudinally and through the axis of rotation (R) in sectional view, which bearing contour(s) are formed of at least two contour sections (44.1 to 44.3; 53.1 to 53.3) to generate fluid dynamic load capacities in both the radial and the axial directions, wherein the bearing surface of the rotor (10) is formed by a rotor part (40), which is connected to a rotor shaft (11) and is secured on the rotor shaft (11), and wherein the rotor part (40) is supported relative to the rotor shaft (11) in the area of a support section (14) of the rotor shaft (11). In order to be able to provide such an exhaust gas turbocharger with a compact and efficient bearing arrangement having a fluid dynamic bearing, wherein at the same time the fluid dynamic bearing can be easily mounted using few parts, provision is made according to the invention that the support section (14) and at least one of the contour sections (53.1 to 53.3) of the counter-bearing part (50) at least sectionally overlap in the direction of the axis of rotation (R).

A seal assembly includes a first and second seats. The first seat includes an axial portion extending circumferentially around a center axis and extending axially from a first end to a second end. A radial portion extends circumferentially around the axial portion and extends radially from the axial portion between the first end and the second end. A cavity is formed in the radial portion and extends circumferentially around the axial portion. A second seat includes a radial segment extending circumferentially around the center axis and extending radially from an inner surface to an outer surface of the radial segment. An axial segment extends circumferentially around the first end of the first seat, and extends axially from the radially segment to a distal end. The axial segment includes a tapered outer surface that tapers radially inward toward the distal end. The distal end is received in the cavity.