A gas turbine engine includes a fan driven by a fan shaft and retractable axial retainer of the shaft mounted on a stator element and movable between a first operational position and a second non-operational position. The retractable axial retainer may include a fluid supply configured for supplying at least one cavity with fluid. In some examples, the retractable axial retainer is mounted movably or slidingly so as to generate movement of the retractable axial retainer between the operation and non-operational positions.

Provided is a boil-off gas compressor for LNG-fueled vessels using LNG as fuel for a propulsion engine thereof. The boil-off gas compressor includes: compressor housings (24a, 24b) in which impellers (30a, 30b) are rotatably arranged; a motor housing (12) in which a motor (14) is disposed to drive the impellers (30a, 30b); and a bearing (18) for rotatably supporting rotation shafts (16a, 16b), which transfer rotation drive force of the motor (14) to the impellers (30a, 30b). The compressor housings (24a, 24b) may be integrally formed with the motor housing (12).

A compressor system includes a gas compressor with dry gas seals about a driveshaft. The compressor system also includes a fugitive gas system having a gas conduit in fluid communication with a collection cavity in a collector coupled to the gas compressor to receive fugitive gas leaked through a pressurized gas leakage path. The fugitive gas system may be structured for flaring the gas, and includes a pressure control system with an accumulator tank, and a vent line for venting gas pressure and having a backpressure regulator therein. Fugitive combustible gas is conveyed through a flow restriction orifice downstream of the compressor.

A seal housing may comprise an aft flange, an outer diameter (OD) ring and a stopper. The stopper may extend radially inward from a radially inner surface of OD ring. The stopper may be configured to interface with a monobloc carbon seal. The stopper may comprise a circumferential stopping portion and an axial stopping portion. There may be a plurality of the stopper.

Disclosed herein are aspects of a sealing device, as well as a pump using the same. In one embodiment, the sealing device includes an axial sleeve having a first end and a second end, a dynamic seal mounted about the first end of the axial sleeve, the dynamic seal including at least one dynamic seal assembly, each of the at least one dynamic seal assemblies including a diffuser and a static steal mounted about the second end of the axial sleeve, and a fixed cartridge housing enclosing at least a portion of the axial sleeve, and an entirety of the dynamic seal and static seal.

A turbo compressor assembly of a cooling machine has a shaft mounted in a common housing with first and second radial dynamic gas bearings and a thrust bearing. A supply stream of working gas supplied to the first radial bearing is formed between an inner wall of a compressor body and the shaft, and a supply stream of working gas from a turbo expander supplied to the second radial bearing and to the thrust bearing is formed between an inner wall of a turboexpander body and the shaft. The first radial dynamic gas bearing is sealed towards the electric motor rotor by a shaft seal. A surface in a shape of an annulus is formed on the shaft between the first radial bearing and the shaft seal, the annulus perpendicular to an axis of the shaft and functioning as a piston for balancing an axial force acting on the shaft.

A turbo compressor of an exhaust gas recirculation of an internal combustion engine, with a compressor housing, a compressor rotor, a shaft that is coupled to the compressor rotor and mounted in the compressor housing, a piston ring seal to prevent an exhaust gas blow-by flow in the direction of bearings, and a labyrinth seal, which seen in the direction of the exhaust gas blow-by flow, is positioned upstream of the piston ring seal.

A seal for a rotor stack includes a first portion that includes a shaft contact surface. A second portion includes a rotor disk contact surface. A transition portion connects the first portion and the second portion. The transition portion extends radially outward from the first portion.

A magnetic bearing centrifugal compressor includes a magnetic bearing spindle having a thrust disk, front and rear axial bearings, an impeller and at least one labyrinth seal. The front and the rear axial bearings are disposed individually to opposing sides of the thrust disk. First and second clearances exist axially between the rear and front axial bearings, respectively, and the thrust disk. The impeller connects a front end of the magnetic bearing spindle. The labyrinth seal pairs the magnetic bearing spindle into an oblique arrangement with respect to the axial direction, and each the labyrinth seal is spaced from the magnetic bearing spindle or the impeller by a labyrinth-seal clearance. By controlling the thrust disk axially, a clearance ratio of the first clearance to the second clearance can be varied to adjust the labyrinth-seal clearance. In addition, a magnetic bearing centrifugal compressor controlling method is also provided.

The gas seal column pump may comprise a pump drive, a gas seal column, a seal gas control box, and a pump. A drive motor of the pump drive, the gas seal column, and the pump may comprise a hermetically sealed, vertically-oriented, pumping system where the gas seal column is operable to replace mechanical seals around a drive shaft that couples the drive motor to the pump. A pressurized seal gas pumped into the drive motor and the gas seal column may displace corrosive fumes and the product being pumped. A product level may be sensed using a plurality of level sensors. Responsive to inputs from the level sensors, a seal gas control box may regulate the pressure of the seal gas using a plurality of valves. A bearing shaft adapter may be added to provide a special drive shaft of other lengths, diameters, or materials.