The invention relates to a side-channel compressor (1) for a fuel cell system (37) for conveying and/or compressing a gas, particularly hydrogen, comprising a housing (3), the housing (3) comprising a housing upper part (7) and a housing lower part (8), a compressor chamber (30) located in the housing (3), comprising at least one peripheral side channel (19), a compressor wheel (2) arranged in the housing (3), which is rotatably arranged about an axis of rotation (4), the compressor wheel (2) comprising blades (5) arranged on the periphery thereof in the region of the compressor chamber (30), and respectively a gas inlet (14) embodied in the housing and a gas outlet (16) which are fluidically interconnected by means of the compressor chamber (30), particularly the at least one side channel (19). According to the invention, the compressor wheel (2) comprises a peripheral stop ring (11) on the periphery thereof, which extends around the compressor wheel (2) in a rotationally symmetric manner in relation to the axis of rotation (4).

The invention relates to a side-channel machine having a housing (4a), located in the housing (4a) a side-channel (28) for guiding a gas, and at least one gas inlet opening (34) which is formed in the housing (4a) and is fluidically connected to the side-channel (28). Furthermore, the side-channel machine has at least one gas inlet pipe (29a) which connects to the at least one gas inlet opening (34), The side-channel machine further comprises at least one gas outlet opening (33) and at least one gas outlet pipe (31a) which connects to the at least one gas outlet opening (33). Furthermore, the side-channel machine has an impeller that can be made to rotate in the housing (4a), with impeller blades, which bound impeller cells arranged in the side-channel (28), for delivering the gas in the impeller cells from the at least one gas inlet opening (34) to the at least one gas outlet opening (33). The side-channel machine further has at least one interrupter (39) arranged between the at least one gas inlet opening (34) and the at least one gas outlet opening (33).

A structural assembly for a fluid-flow machine includes: a main flow path boundary and at least one row of relatively rotating blades with a gap existing between blade ends of the at least one row of blades and the main flow path boundary. At least one secondary flow duct has in the main flow path boundary one opening each at ends spaced apart in the flow direction, such that the secondary flow duct is connected to the main flow path via the two openings. The structural assembly has at least two components connected to one another, i.e. at least one support component and at least one connecting component, where the support component at least partially forms the main flow path boundary and where the connecting component forms or surrounds at least one part-section of the secondary flow duct.

The invention relates to a side-channel machine having a housing (4a), located in the housing (4a) a side-channel (28) for guiding a gas, and at least one gas inlet opening (34) which is formed in the housing (4a) and is fluidically connected to the side-channel (28). Furthermore, the side-channel machine has at least one gas inlet pipe (29a) which connects to the at least one gas inlet opening (34). The side-channel machine further comprises at least one gas outlet opening (33) and at least one gas outlet pipe (31a) which connects to the at least one gas outlet opening (33). Furthermore, the side-channel machine has an impeller that can be made to rotate in the housing (4a), with impeller blades, which bound impeller cells arranged in the side-channel (28), for delivering the gas in the impeller cells from the at least one gas inlet opening (34) to the at least one gas outlet opening (33). The side-channel machine further has at least one interrupter (39) arranged between the at least one gas inlet opening (34) and the at least one gas outlet opening (33).

The invention relates to a side-channel machine having a housing (4a), located in the housing (4a) a side-channel (28) for guiding a gas, and at least one gas inlet opening (34) which is formed in the housing (4a) and is fluidically connected to the side-channel (28). Furthermore, the side-channel machine has at least one gas inlet pipe (29a) which connects to the at least one gas inlet opening (34), The side-channel machine further comprises at least one gas outlet opening (33) and at least one gas outlet pipe (31a) which connects to the at least one gas outlet opening (33). Furthermore, the side-channel machine has an impeller that can be made to rotate in the housing (4a), with impeller blades, which bound impeller cells arranged in the side-channel (28), for delivering the gas in the impeller cells from the at least one gas inlet opening (34) to the at least one gas outlet opening (33). The side-channel machine further has at least one interrupter (39) arranged between the at least one gas inlet opening (34) and the at least one gas outlet opening (33).

This centrifugal rotary machine includes an impeller having a disk, blades, and a cover. The centrifugal rotary machine further includes a casing which accommodates the impeller radially inward and forms a gap between an outer circumferential surface of the cover and the casing. The centrifugal rotary machine further includes a sealing device which seals the gap. The casing includes an end wall surface which is disposed to face one axial side of a cover end surface facing one axial side of the cover, extends in the radial direction and forms a radial flow path between the end wall surface and the cover end surface. The casing further includes a foreign matter introduction path which is formed inside the casing and communicates with a radially outer side of the radial flow path.

Flow restricting arrangements and rotor assemblies are provided. A flow restricting arrangement includes a stationary component and a rotating component. The rotating component is radially spaced apart from the stationary component such that a clearance is defined between the stationary component and the rotating component. A first magnet is embedded within the stationary component. A second magnet embedded within the rotating component. A plurality of magnetically responsive particles is contained within the clearance by a magnetic field produced by the first magnet and the second magnet. The plurality of magnetically responsive particles at least partially span the clearance.

A small gas turbine engine, such as is used to power a UAV, that includes at least one centrifugal compressor having an impeller with blades that form a gap between the blade tips and stationary shroud of the gas turbine engine, and where a resistance heating element is secured to or bonded to a compressor casing of the gas turbine engine in order to use heat to control the gap between the impeller blades and the stationary shroud. The resistance heating element is activated at cruise mode to move the shroud toward the impeller. Additionally or alternatively, the compressor casing is heated with bled-off compressed air to move the shroud toward the impeller. A capacitance tip clearance sensor can be mounted on the impeller shroud to monitor and control tip clearance in real time.

The invention relates to a side-channel machine having a housing (4a), located in the housing (4a) a side-channel (28) for guiding a gas, and at least one gas inlet opening (34) which is formed in the housing (4a) and is fluidically connected to the side-channel (28). Furthermore, the side-channel machine has at least one gas inlet pipe (29a) which connects to the at least one gas inlet opening (34), The side-channel machine further comprises at least one gas outlet opening (33) and at least one gas outlet pipe (31a) which connects to the at least one gas outlet opening (33). Furthermore, the side-channel machine has an impeller that can be made to rotate in the housing (4a), with impeller blades, which bound impeller cells arranged in the side-channel (28), for delivering the gas in the impeller cells from the at least one gas inlet opening (34) to the at least one gas outlet opening (33). The side-channel machine further has at least one interrupter (39) arranged between the at least one gas inlet opening (34) and the at least one gas outlet opening (33).

A small gas turbine engine, such as is used to power a UAV, that includes at least one centrifugal compressor having an impeller with blades that form a gap between the blade tips and stationary shroud of the gas turbine engine, and where a resistance heating element, such as an impingement air manifold, is secured to or bonded to a compressor casing of the gas turbine engine in order to use heat to control the gap between the impeller blades and the stationary shroud. The resistance heating element is activated at cruise mode to move the shroud toward the impeller. Additionally or alternatively, the compressor casing is heated with bled-off compressed air to move the shroud toward the impeller. A capacitance tip clearance sensor can be mounted on the impeller shroud to monitor and control tip clearance in real time.