A vacuum pump comprises an inlet flange for connecting to a vacuum chamber, where the inlet flange comprises a plurality of apertures for receiving a plurality of protruding fixing elements extending from the vacuum chamber. The protruding fixing elements comprise an enlarged retaining portion at an end remote from the vacuum chamber and a fastener receiving portion having at least one radial dimension that is smaller than a corresponding dimension of the enlarged retaining portion. A fastening mechanism is provided that comprises a plurality of slots each extending from a same side of a plurality of apertures. The fastening mechanism is configured to be rotatable between a mounting position in which the apertures are aligned with the protruding fixing elements and a sealing position in which the slots are aligned with the protruding fixing elements.

Provided are a vacuum pump and an adapter used in the vacuum pump that are capable of responding to various changes in specifications at low cost. A turbo-molecular pump includes a base, a stator blade that is provided above the base in an axial direction of a rotor, a rotor blade that is integrally attached to the rotor, a housing that is formed in a cylindrical shape, and accommodates the stator blade and is integrally attached to the base, and an adapter that is replaceable depending on a type of the stator blade, the rotor blade, or the housing, and that is detachably mounted on the base and is configured to support the stator blade in the axial direction.

A turbine engine for an aircraft can includes a casing. The casing can be a fan casing surrounding a fan assembly for drawing air into the turbine engine. The fan casing can have a peripheral wall. A surface cooler can be provided in the turbine engine confronting the peripheral wall of the fan casing. The surface cooler can have a mounting bracket for mounting the surface cooler to the fan casing.

A portable blowing device configured for being worn around a neck of a human body, includes two arms each defining an airflow channel therein; and fans received in the arms respectively. The arm includes an inner side wall close to the neck and an outer side wall connected to the inner side wall. The arm includes an air inlet and an air outlet in communication with the airflow channel respectively. The air inlet is arranged at the inner side wall and/or the outer side wall. The fan is configured to generate an airflow passing through the air inlet, the airflow channel and the air outlet in sequence.

The invention relates to a method of installing a subsea system (1) comprising the steps of: —installing at least one first foundation structure (13′) on a seabed, wherein the first foundation structure (13′) comprises a connection interface (50′) connectable to a second foundation structure (13″), —installing a first compressor train on the foundation structure (13′), the first compressor train comprising at least a first compressor (8′), —connecting the first compressor train to at least one well flow line (2), —connecting a first compressed fluid line (9′) to an outlet (15′) of the first compressor (8′) and to a common outlet (16) for the compressed fluid in the subsea system (1), wherein the first compressed fluid line (9′) comprises a flow regulating device (24′), —connecting a first connection line (10′,12′) to the first compressed fluid line (9′) at a position upstream of the flow regulating device (24′) and/or to a line (2, 6′) at a position upstream of the first compressor (8), and wherein the first connection line (10′, 12′) is connectable to an additional compressor train positioned on the second foundation structure (13″), the first connection line (10′) comprising a flow regulation device (20′,22′), —connecting a second connection line (11′) to the first compressed fluid line (9′) at a position downstream of the flow regulation device (24′) and wherein the second connection line (11′) is connectable to the additional compressor train positioned on the second foundation structure (13″), the second connection line (11′) comprising a flow regulation device (21′). It is further described an associated a subsea system.

A vacuum pump and a piping structural portion for a vacuum pump are provided that limit damage to a component connected to external piping and limit gas leakage even when the vacuum pump is displaced in a rotation direction due to damage to the vacuum pump. The vacuum pump draws in gas through an inlet port by rotation of a rotor and includes a casing, which rotatably houses the rotor, and a piping structural portion disposed in the casing. At least a part of the piping structural portion includes an elastic portion that is configured to elastically deform to absorb a displacement.

A mounting base of a ceiling fan has a mounting disc, a fitting sleeve, and a positioning unit. The mounting disc has a through hole. The fitting sleeve is mounted in the through hole and has a hanging block located on an end of the fitting sleeve. The fitting sleeve is hung on the mounting disc via the hanging block. An accommodating space is formed through the fitting sleeve and is adapted to accommodate a hanging rod. The positioning unit is mounted in the accommodating space and is capable of engaging with the hanging rod. The positioning unit has a bending edge. The positioning unit is hung on the fitting sleeve via the bending edge. The mounting base has a simplified assembling process and a great stability in mounting structure.

A rotating assembly for a gas turbine engine has a balancing ring mounted to a first rotating component having a rotating unbalance about an axis of rotation. The ring is clocked at a circumferential position about the axis to counteract the rotating unbalance. A spacer is axially abutted against the first rotating component to set an axial position of the first rotating component relative to a second rotating component. The balancing ring is locked against rotation relative to the first rotating component in its circumferential position by the dual use spacer.

A compressor may include a compression mechanism and a shell assembly. The shell assembly may include first and second snap rings, a body, and first and second caps cooperating with the body to enclose the compression mechanism therein. The body may include first and second ends and an inner surface extending between both ends. The first cap may be received within the first end and may include a first side wall having a first groove. The second cap may be received within the second end and may include a second side wall having a second groove. The first snap ring may be disposed within the first groove and may engage the first end to restrict removal of the first cap from the body. The second snap ring may be disposed within the second groove and may engage the second end to restrict removal of the second cap from the body.

The invention relates to part of a turbine engine comprising two arms passing through a stream of the turbine engine, wherein each arm comprises an outer surface and an aerodynamic linking device. The aerodynamic linking device comprises fairings extending between the two arms, compressible interface means interposed between the fairings and means for retaining the fairings in place by pressure in relation to the arms, which compress the interface means.