A circumferential seal assembly capable of separating a gas into two separate flow paths before communication between a rotatable runner and a pair of seal rings is presented. The seal assembly includes an annular seal housing, a pair of annular seal rings, a rotatable runner, and a plurality of groove structures. The seal housing is interposed between a pair of compartments. The seal rings are separately disposed within the seal housing and separately disposed around the rotatable runner. The groove structures are disposed along an outer annular surface of the rotatable runner. A gas is communicable onto the groove structures. Each groove structure includes at least two hydrodynamic grooves that separate and communicate the gas onto the seal rings. Each groove includes steps whereby the depth of at least one adjoining step decreases in the direction opposite to rotation with or without the depth of another adjoining steps increasing in the direction opposite to rotation. Each groove is also tapered widthwise.

The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction extended from an axial centerline, and a circumferential direction. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in serial flow arrangement along the longitudinal direction. The gas turbine engine includes a low speed turbine rotor including a hub extended along the longitudinal direction and radially within the combustion section; a high speed turbine rotor including a high pressure (HP) shaft coupling the high speed turbine rotor to a HP compressor in the compressor section; and a first turbine bearing disposed radially between the hub of the low speed turbine rotor and the HP shaft. The HP shaft extends along the longitudinal direction and radially within the hub of the low speed turbine rotor. The high speed turbine rotor defines a turbine cooling conduit extended within the high speed turbine rotor. The first turbine bearing defines an outer air bearing along an outer diameter of the first turbine bearing and adjacent to the hub of the low speed turbine rotor. The first turbine bearing defines an inner air bearing along an inner diameter of the first turbine bearing and adjacent to the HP shaft. The first turbine bearing further defines a cooling orifice adjacent along the longitudinal direction to the turbine cooling conduit of the high speed turbine rotor. The cooling orifice and the turbine cooling conduit are in fluid communication.

A throttle unit is equipped with a grooved block including at least one minute groove formed on a plane surface, and an opposite block having a plane surface which is opposite to the minute groove. The grooved block and the opposite block are detachably joined so as to be opposite to each other. A throttle fluid path is formed by the minute groove and the plane surface of the opposite block. At least one surface of each of the minute groove is constituted by a curved surface or an inclined surface that is inclined with respect to the plane surface of the grooved block.

A self-metering hydrostatic thrust bearing for a small gas turbine engine. The thrust bearing can provide thrust capacity in the fore and aft directions of a hydrostatic thrust bearing using a single source of air. The air supply is directed towards the loaded bearing and away from the unloaded bearing by the self-metering mechanism operated by the thrust load.

A bearing assembly including a body defining an outer surface, an inner surface, and an aft surface is generally provided. A first inlet opening is defined through the outer surface in fluid communication with a first internal passage defined by a first internal wall. The first internal passage is in fluid communication with a first outlet opening defined through the inner surface. A second inlet opening is defined through the inner surface in fluid communication with a second internal passage defined by a second internal wall. The second internal passage is in fluid communication with a second outlet opening defined through the aft surface.

The various technologies presented herein relate to fabrication and operation of a heat exchanger that is configured to extract heat from an underlying substrate. Heat can be extracted by way of an air gap formed between an impeller and a baseplate. By utilizing a pump to create an initial air gap that is further maintained by rotation of the impeller relative to the baseplate, a spring can be utilized that can apply a force of greater magnitude to the impeller than is used in a conventional approach, thus enabling the weight of the impeller to be negligible with respect to a width of the air gap, thereby conferring the desirable feature of orientation independence with respect to gravity with no performance degradation.

The various technologies presented herein relate to fabrication and operation of a heat exchanger that is configured to extract heat from an underlying substrate. Heat can be extracted by way of an air gap formed between an impeller and a baseplate. By utilizing a pump to create an initial air gap that is further maintained by rotation of the impeller relative to the baseplate, a spring can be utilized that can apply a force of greater magnitude to the impeller than is used in a conventional approach, thus enabling the weight of the impeller to be negligible with respect to a width of the air gap, thereby conferring the desirable feature of orientation independence with respect to gravity with no performance degradation.

In an aerodynamic bearing, an outer peripheral surface of a shaft and an inner peripheral surface of a sleeve face each other in a radial direction. The sleeve includes a through hole penetrating the sleeve in the radial direction. A space on a radially inner side of the sleeve communicates with an external space of a motor through the through hole. A stationary portion includes a wall portion radially overlapping the through hole with a gap interposed therebetween on a radially outer side of the through hole.

An apparatus for conveying a substrate includes a base along which the substrate is conveyed, a first upward gas ejecting section, a second upward gas ejecting section and a third upward gas ejecting section disposed over the base, the third upward gas ejecting section being disposed between the first and second upward gas ejecting sections, and a first downward gas ejecting section and a second downward gas ejecting section disposed above and facing respective portions of the third upward gas ejecting section. Gas ejected upward from the first, second and third upward gas ejecting sections floats the substrate. The substrate is subjected to pressure by gas ejected downward from the first and second downward gas ejecting sections. The first and second downward gas ejecting sections are spaced to provide a working area therebetween and through which the substrate is irradiated with a laser beam.

The present disclosure provides a split-type swing angle adjustable aerostatic bearing device for rotor static balance and an air flotation support device for static balance of rotating ring-shaped parts, the split-type swing angle adjustable aerostatic bearing device for rotor static balance and an air flotation support device for static balance of rotating ring-shaped parts belong to a field of static balance detection, and aims to solve a problem of low measurement precision of rotor and realize static balance of rotating ring-shaped parts. A gas mold, having a certain bearing capacity, is formed between an outer surface of the air flotation support cover under the bearing base and a concave surface of the upper base, so that the bearing base is floated to realize an automatic centering of the rotor static balancing device.