In a turbine rotor blade assembly 1 of the present invention, each turbine rotor blade 10 includes a platform 11 having a blade root 12 fixed to a turbine disk 30, a profile 13 rising from the platform 11, and a shroud 14 provided at a top end of the profile 13. The shroud 14 of the present invention includes a first contact end part 15 that comes into contact with an adjacent shroud adjacent to one end side in a circumferential direction, a second contact end part 16 that comes into contact with an another adjacent shroud adjacent to the other end side in the circumferential direction, and a main body part disposed between the first and second contact end parts 15 and 16. One or both of the first and second contact end parts 15 and 16 are lower in rigidity than the main body part.

A method for modifying an airfoil shroud located at a tip of an airfoil is provided. A locating step locates a reference location in a first end edge. The reference location includes a portion of a fillet. A seal rail extends circumferentially along a radially outer surface of the airfoil shroud. The fillet extends along the radially outer surface and is positioned directly adjacent to the seal rail. A forming step forms a compound relief cut in the fillet without performing a weld process on the airfoil shroud to remove the reference location. The compound relief cut has a first cut having a first radius extending from the seal rail towards the first end edge, and a second cut having a second radius extending from an end of the first cut to the first end edge. Modifying the airfoil shroud is complete following forming the compound relief cut.

An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.

An oil-lubricated, tapered-land thrust bearing assembly (60) for automotive turbochargers (10) including a thrust bearing (30). The thrust bearing (30) includes an assembly of a base (62) with at least one insert (64 or 66), which is designed to control the oil film as a purposefully compliant structure based on applied force to optimize performance at low and high power operation. The ramp angle is relatively large at a low load and decreases to a smaller ramp angle at higher loads. On one side of the turbocharger (10), the thrust bearing assembly (60) may operate with a flinger sleeve (34) and a thrust washer (24) within a complementary bearing housing cover (32).

Provided is a slide device which includes a fixed-side slide member having an annular-shaped first slide surface, and a rotary-side slide member having an annular-shaped second slide surface, with the slide device being configured such that the first slide surface and the second slide surface are positioned opposite to each other, and an outer peripheral side of the fixed-side slide member and an outer peripheral side of the rotary-side slide member are brought into contact with a liquid containing a blood component, and a region where the first slide surface and the second slide surface face each other along the rotary-side slide member, the first slide surface and the second slide surface are brought into contact with each other on an outermost periphery of the opposite-facing region of the first and second slide surfaces.

A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.

A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon connecting portion and extending in the aft direction from the first annular portion. A second annular portion, aft of the first annular portion and coupled to the rail, is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage with the first annular portion when the second annular portion is in the closed position, thereby providing access to the engine core. A guide pin extends forward from the second annular portion. A locking mechanism is disposed within the first annular portion for engaging the guide pin when the second annular portion is in the closed position.

An exhaust-gas turbocharger (1) having a compressor (2), which has a compressor housing (3); a turbine (4), which has a turbine housing (5): and a bearing housing (6), which is arranged between the compressor housing (3) and the turbine housing (5) and is connected to the compressor housing (3) by way of a compressor-side connecting device and to the turbine housing (5) by way of a turbine-side connecting device (7). The turbine housing-side and/or compressor-side connecting device (7) is in the form of a taper key bolted joint having bolts (8, 9, 10) which are arranged at least substantially perpendicularly to an exhaust-gas turbocharger longitudinal axis (L).

A turbocharger (1) having a turbine housing (2), a compressor housing (3) which has a compressor outlet (20), and a silencer (21) which is arranged on an end region (22) on the compressor outlet (20) and which has a silencer housing (23) in which an insert part (25) is arranged so as to form at least one buffer chamber (24) which is connected via at least one opening (26) to an air-guiding duct (27). The opening (26) has an edge (28) with a radially inner corner (29) which is designed so as not to have a sharp edge.

A gas turbine engine includes a core, a first annular portion, a rail, and a second annular portion. The first annular portion is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion, and a fore bi-fi. The rail is coupled to the fore pylon portion and extending in the aft direction from the stationary portion. The second annular portion is arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion comprises an aft bi-fi configured to engage with the fore bi-fi when the gas turbine engine is in the closed position.