A turbomachine assembly and, in particular, a low-pressure compressor of an aircraft turbojet engine includes an annular row of upstream vanes with trailing edges extending radially from an upstream support; an annular row of downstream vanes with leading edges axially facing the trailing edges and extending radially from a downstream support; an annular passageway delimited by the upstream support and the downstream support. The downstream support has a profile with: an upstream portion delimiting the annular passageway forming an annular slide, a downstream portion axially at the level of downstream vanes, and a connecting arc connecting the upstream portion to the downstream portion. The connecting arc is arranged downstream of the leading edges.

In a turbocharger for receiving exhaust gas from an internal combustion engine and for delivering compressed air to the internal combustion engine, a backplate may include a lubricant stall protrusion, such as a rib, may be placed in recirculation or collection recesses of the backplate to stall recirculating lubricant flow and direct the lubricant into a bearing housing lubricant core and drain to reduce an amount of lubricant proximate piston rings and leaking into a compressor housing of the turbocharger. When an lubricant deflector is used, the lubricant stall protrusion stalls recirculating lubricant that is outboard of the lubricant deflector, and may have an outer protrusion edge closely matching the outboard contour of the lubricant deflector to minimize a flow gap there between.

An assembly is provided for a piece of rotational equipment. This assembly includes a stationary component, a rotating component, and a dry seal assembly. The dry seal assembly is configured to substantially seal an annular gap between the stationary component and the rotating component. The dry seal assembly includes a seal element and a seal land. The seal element is mounted to the stationary component and is configured to sealingly engage the seal land. The seal land is mounted to the rotating component and is configured to permit gas leakage across the dry seal assembly through a passageway in the seal land.

A sealing assembly for sealing between an oil cavity and an air cavity of a gas turbine is provided. The sealing assembly comprising a seal having a seal element and a circumferential seal housing receiving the seal element. The seal housing has an annulus extending circumferentially around a center axis, radially between an outer periphery and an inner periphery, and axially along the center axis between a first surface and a second surface. The seal housing has a collecting channel defined circumferentially in the inner periphery about the center axis and a draining pocket defined in a portion of the seal housing configured and disposed to in use collect liquid oil during engine operation. The draining pocket extends from the collecting channel to the first surface and configured to communicate collected liquid oil from the collecting channel to the oil cavity.

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.

An on-board injector that delivers discharge air toward a turbine rotor of a gas turbine engine includes a second wall spaced form a first wall to define an annular inlet about an engine longitudinal axis and a multiple of airfoil shapes between the first wall and the second wall to segregate discharge air from the annular inlet, and a multiple of bypass apertures each along a radial axis transverse to the engine longitudinal axis through each of the multiple of airfoil shapes and the respective first wall, the second wall.

A rotor drum for an aircraft turbomachine includes an annular wall extending around a longitudinal axis (A), the annular wall carrying rotor blades and having at least one bleed device configured to allow at least one liquid to pass through the annular wall. The bleed device includes a series of three adjacent circular orifices, the three orifices being aligned along a line and having a central orifice of larger diameter D1 and two lateral orifices of smaller diameter D2 diametrically opposed with respect to the central orifice.

The present invention relates to a gas heat pump system. A gas heat pump system according to one embodiment of the present invention comprises: a compressor for compressing a refrigerant; a gas engine for driving the compressor; a mixer for mixing air and fuel to generate a mixed gas to be supplied to the gas engine; a mixed gas supply line connected between the mixer and the gas engine; and a supercharger for supercharging the mixed gas supplied to the gas engine through the mixed gas supply line, wherein the supercharger comprises a sealed housing formed by sealing the remaining parts thereof other than an inlet port and an outlet port through which the mixed gas moves into and out of the housing, and a bypass line is provided between the sealed housing and the inlet port of the supercharger so as to resupply a mixed gas in the sealed housing to the inlet port of the supercharger. Therefore, the system can prevent a safety-related accident resulting from the leakage of the mixed gas out of the supplier and can reduce the amount of fuel consumption.

A side-channel compressor (1) for a fuel cell system (37) for conveying and/or compressing a gas, in particular hydrogen, having a housing (3), having a compressor chamber (30) which is situated in the housing (3) and which has two encircling side channels (19, 21), having a compressor impeller (2) which is situated in the housing (3) and which is arranged so as to be rotatable about an axis of rotation (4), wherein the compressor impeller (2) has conveying cells (28) arranged at the circumference thereof and in the region of the compressor chamber (30), and having in each case one gas inlet opening (14) formed on the housing (3) and one gas outlet opening (16), which openings are fluidically connected to one another via the compressor chamber (30), in particular the two side channels (19, 21), and wherein, in the region of the compressor chamber (30), an encapsulation of the respective side channel (19, 21) is realized by at least one separation region (35) by means of a surface pairing of the compressor wheel (2) and of the housing (3). According to the invention, here, the at least one separation region (35) is formed by a surface pairing of the components compressor impeller (2) and housing (3) such that the respective one component has encircling edges (5), in particular with encircling tips (11), and the respective other component has an encircling, at least approximately planar counterpart surface (23).

In order to compensate for the increase in a leakage rate of ventilation air originating in a circuit via a labyrinth seal that gradually wears at the bottom of a ventilation chamber, and the reduction of a purge rate via an opening upstream from the chamber, a second injection opening is added to a main injection opening. The second injection opening communicates with the chamber via a second labyrinth seal that wears at the same time as the first, and thus gradually increases the air flow rate passing through the injector in order to compensate for the additional leakage rate through the first injector and maintain the ventilation at its initial level.