An oil seal structure and a compressing apparatus including the oil seal structure are provided. The oil seal structure includes a rotating shaft, a bearing, a lower housing portion, an upper housing portion, an assembly surface seal member inserted into a first assembly surface seal groove, and an oil seal member provided in a first seal groove and a second seal groove and including a flange portion, wherein a lower oil receiving portion is formed in the lower housing portion, a first passage groove is formed in the first seal groove, and an oil passage is formed between a bottom surface of the first passage groove and the flange portion.

A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.

A countercurrent heat recovery ventilation system includes an air module assembly and heat exchanger assembly. Air module assembly made from front and back panels connected by two side panels, base plate fixed with the side panels and placed parallel between side panels and a double side radial impeller with a shaft, an electric drive form two hydraulically isolated flow canals with inlet and outlet openings.

The heat exchanger assembly comprises a heat-exchanger that could be done as changeable flow side heat-exchanger made as folded corrugated fins or plates, thus each of the both flow passages split in separate flow channels. Every other channel is sealed to flow from flow same direction forcing the flow to be in opposite direction in all adjacent cannels. This forms two hydraulically isolated flow passages with intake and outtake openings connected respectively with outlet and inlet openings of the air blower assembly.

A phase adjustment system 100 for a geared compressor 1 includes a phase adjustment jig 50 that is to be detachably provided in the geared compressor 1. The geared compressor 1 includes a drive gear 4 fixed to a drive shaft and having a largest outer diameter among a plurality of gears; a driven gear having a smaller diameter than a diameter of the drive gear 4 and meshing with the drive gear 4; and a gear casing accommodating the drive gear 4 and the driven gear. The phase adjustment jig 50 includes a fifth jig gear 66 that meshes with the drive gear 4 in a state where a frame 51 is fixed to the gear casing; and a manually rotatable handle 70 that is configured to rotate the fifth jig gear 66.

A multi-stage compressor system is a system of a multi-stage compressor in which compressors are connected in series in a plurality of stages includes a control unit. The control unit determines whether a malfunction is present in the system by comparing a suction flow rate of a first-stage compressor measured by a first sensor with a downstream flow rate from an outlet of the multi-stage compressor measured by a second sensor.

A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.

A rotary machine includes a first impeller which rotates about an axis integrally with a rotating shaft, and a casing which covers the rotating shaft and the first impeller. The first impeller includes a circular-disk-shaped first disk part centered on the axis, a plurality of blade parts which extend from a surface facing a first side of the first disk part in an axial direction toward the first side in the axial direction and disposed at intervals in a circumferential direction, and an extension shaft which extends from a surface facing a second side of the first disk part in the axial direction toward the second side in the axial direction centered on the axis. An end portion of the extension shaft on the second side in the axial direction is connectable to an end portion of the rotating shaft on the first side in the axial direction.

A geared turbo machine having a transmission, a drive assembly and multiple output assemblies. The transmission has a central bull gear and multiple pinions engaging into the bull gear. A first output assembly a two-stage main compressor in which a process gas is compressed using the mechanical drive power provided by the drive assembly a respective intermediate cooler is connected between two respective stages of the main compressor to cool the second process gas. A respective intermediate cooler is arranged between the last stage of the main compressor and a first output assembly and between two respective output assembly and an end cooler arranged downstream of the last. Each intermediate cooler and the end cooler has a respective housing with a supply connector and a discharge connector and a heat exchanger At least one intermediate cooler and/or the end cooler has a heat exchanger with a plate-type construction.

A multi-stage, intercooled centrifugal compressor with integral power generator system for a mobile, ground-based aviation support cart is disclosed. A bootstrap-type turbo compressor module which can supply cooled air. The system may be operated in one of several modes: high pressure bleed air (e.g., 35-50 psig) for jet engine start, conditioned or cooled air (e.g., 2-5 psig) for aircraft cooling purposes, or electrical ground power. Electrical ground power and conditioned air may also be supplied simultaneously if desired.

A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.