Abstract: A compressor wheel (1) of a compressor (6A) of an exhaust-gas turbocharger (6), having a hub (2); and having a multiplicity of non-recessed blades (3) which are arranged on the hub (2) and which have in each case a blade leading edge (3A) and a blade trailing edge (3B). The blade leading edges (3A) define an inlet area (A1) which is the area swept by the blade leading edges (3A) as the compressor wheel (1) rotates. The blade trailing edges (3B) define an outlet area (A2) which is the area swept by the blade trailing edges (3B) as the compressor wheel (1) rotates. The ratio A2/A1 is >60%.

Abstract: An air feed device (1) for a fuel cell, having a shaft (2); a compressor wheel (4) fastened to one of the ends (5, 20) of the shaft (2), a bearing arrangement (6, 7, 8) arranged in a bearing housing (9) for mounting the shaft (2), and an electric motor (10) for driving the shaft (2), which electric motor is arranged in the bearing housing (9). The shaft (2) has two shaft bearing portions (11, 12) and a magnet portion (13) arranged between the shaft bearing portions (11, 12), forming the rotor of the electric motor (10). The shaft bearing portions (11, 12) and the magnet portion (13) are centered relative to one another by means of a centering arrangement (12A, 13F) which engages on an outer edge (A), the shaft bearing portions (11, 12) and the magnet portion (13) bearing in each case axially against one another.

Abstract: A compressor (1) of an exhaust-gas turbocharger (ATL), having a compressor wheel (2) and a compressor housing (3) which has a housing longitudinal axis (A). The compressor wheel (2) is arranged in the housing. An inlet duct (5) runs from a compressor inlet (4) to the compressor wheel (2). A recirculation duct (6) has a compressor-wheel-side inflow opening (7) and a compressor-inlet-side return flow opening (8). The inflow opening (7) and the return flow opening (8) can be opened and closed.

Abstract: A compressor wheel (1) of a compressor (6A) of an exhaust-gas turbocharger (6), having a hub (2); and having a multiplicity of non-recessed blades (3) which are arranged on the hub (2) and which have in each case a blade leading edge (3A) and a blade trailing edge (3B). The blade leading edges (3A) define an inlet area (A1) which is the area swept by the blade leading edges (3A) as the compressor wheel (1) rotates. The blade trailing edges (3B) define an outlet area (A2) which is the area swept by the blade trailing edges (3B) as the compressor wheel (1) rotates. The ratio A2/A1 is >60%.

Abstract: An air feed device (1) for a fuel cell, having a shaft (2); a compressor wheel (4) fastened to one of the ends (5, 20) of the shaft (2), a bearing arrangement (6, 7, 8) arranged in a bearing housing (9) for mounting the shaft (2), and an electric motor (10) for driving the shaft (2), which electric motor is arranged in the bearing housing (9). The shaft (2) has two shaft bearing portions (11, 12) and a magnet portion (13) arranged between the shaft bearing portions (11, 12), forming the rotor of the electric motor (10). The shaft bearing portions (11, 12) and the magnet portion (13) are centered relative to one another by means of a centering arrangement (12A, 13F) which engages on an outer edge (A), the shaft bearing portions (11, 12) and the magnet portion (13) bearing in each case axially against one another.

Abstract: A compressor (1) of an exhaust-gas turbocharger (ATL), having a compressor wheel (2) and a compressor housing (3) which has a housing longitudinal axis (A). The compressor wheel (2) is arranged in the housing. An inlet duct (5) runs from a compressor inlet (4) to the compressor wheel (2). A recirculation duct (6) has a compressor-wheel-side inflow opening (7) and a compressor-inlet-side return flow opening (8). The inflow opening (7) and the return flow opening (8) can be opened and closed.

Abstract: A housing (410, 510, 610, 700, 800, 900) for a turbocharger (400, 500, 600) is provided. The housing (410, 510, 610, 700, 800, 900) has an impeller chamber (403, 503, 603), diffuser (450, 550, 650, 750, 850, 950) and scroll (420, 520, 620, 720, 820, 920) in fluid communication with each other. The diffuser (450, 550, 650, 750, 850, 950) can have a curved shape and/or a bend (455) in proximity to a tip (408, 508, 608, 609) of the impeller (405, 505, 605). The curved shape can be defined by one or more radii of curvature (RC, RC1, RC2). The diffuser (450, 550, 650, 750, 850, 950) can extend in a radial direction that is non-orthogonal to the center line of the turbocharger (400, 500, 600). The housing (410, 510, 610, 700, 800, 900) can be for a compressor section of the turbocharger (400, 500, 600).

Abstract: A housing (410, 510, 610, 700, 800, 900) for a turbocharger (400, 500, 600) is provided. The housing (410, 510, 610, 700, 800, 900) has an impeller chamber (403, 503, 603), diffuser (450, 550, 650, 750, 850, 950) and scroll (420, 520, 620, 720, 820, 920) in fluid communication with each other. The diffuser (450, 550, 650, 750, 850, 950) can have a curved shape and/or a bend (455) in proximity to a tip (408, 508, 608, 609) of the impeller (405, 505, 605). The curved shape can be defined by one or more radii of curvature (RC, RC1, RC2). The diffuser (450, 550, 650, 750, 850, 950) can extend in a radial direction that is non-orthogonal to the center line of the turbocharger (400, 500, 600). The housing (410, 510, 610, 700, 800, 900) can be for a compressor section of the turbocharger (400, 500, 600).

Abstract: As air passes through the airflow channels (46) between the blades (10) of a compressor impeller, boundary layers build up on the blade (10) surfaces. These low momentum masses of air are considered a blockage and loss generators. Ultimately, the boundary layer on the suction side of the blade (20) will separate, causing stall and reversed flow. Reversed flow will occur until a stable pressure ratio with positive volume flow rate is reached. When the pressure ratio becomes unstable again, the cycle will repeat. Introducing a slit (12) or a series of perforations (28) on the compressor wheel blade (10) allows the air to communicate between the pressure side (18) and the suction side (20) of the blade, which allows the boundary layer to stay attached longer.

Abstract: As air passes through the airflow channels (46) between the blades (10) of a compressor impeller, boundary layers build up on the blade (10) surfaces. These low momentum masses of air are considered a blockage and loss generators. Ultimately, the boundary layer on the suction side of the blade (20) will separate, causing stall and reversed flow. Reversed flow will occur until a stable pressure ratio with positive volume flow rate is reached. When the pressure ratio becomes unstable again, the cycle will repeat. Introducing a slit (12) or a series of perforations (28) on the compressor wheel blade (10) allows the air to communicate between the pressure side (18) and the suction side (20) of the blade, which allows the boundary layer to stay attached longer.