A tip portion of a compressor blade faces a casing with a clearance therebetween. The tip portion has an upstream-side region including a blade leading edge, and a downstream-side region including a blade trailing edge. The upstream-side region has a small clearance formation portion including a part in which the clearance is a minimum in the tip portion. The downstream-side region forms a large clearance formation portion having a clearance larger than a clearance of the small clearance formation portion throughout the entire region of the downstream-side region.

The present disclosure relates to a fan apparatus (1). The fan apparatus (1) includes an impeller (12A, 12B, 12C, 26A, 26B) for generating a flow of air. A drive means (14) is provided for driving the impeller (12A, 12B, 12C, 26A, 26B). At least in certain embodiments, the drive means (4) includes a turbine (18) adapted to be rotated by a working liquid supplied to the fan apparatus (1). The fan apparatus (1) described herein is suitable for providing air ventilation and/or air extraction, for example.

A compressor airfoil of a gas turbine engine includes a pressure side and a suction side of the airfoil extending downstream from a stagnation point, the suction side including a suction side surface portion within a leading edge region, and a main suction side airfoil surface downstream from the suction side surface portion and extending contiguously therewith. The suction side surface portion having a compound curvature profile which includes at least a leading edge having a first curvature profile and a chamfered surface having a second curvature profile different from the first curvature profile. The chamfered surface being contiguous with and extending immediately downstream from the leading edge. The first curvature profile being curved. The second curvature profile of the chamfered surface being substantially flat and defining a substantially straight-line profile in a cross-section transverse to the span-wise axis of the airfoil.

A disc turbocharger includes a multi-disc engine in which each disc engine includes a turbine blade, a compressor blade, and a bearing without requiring a shaft between the turbine blade and the compressor blade. The power produced by each turbine blade is consumed by its own joined compressor. The disc turbocharger has a multi-disc engine that works as a multi-stage turbocharger with a smaller size and no piping between the turbochargers. The disc turbocharger uses a waste spool valve for control of the.

A compressor or pump stage is provided. The compressor or pump stage at least comprising a central shaft (8) and one rotor (3), where the axis of rotation of the rotor (3) is the central shaft (8) and where the rotor comprises a number, n, of rows of impellers (5) arranged at an outer perimeter of the rotor with an axial distance between neighbouring rows of impellers (5), where n={2, 3, 4 . . . }.

A disc turbocharger includes a multi-disc engine in which each disc engine includes a turbine blade, a compressor blade, and a bearing without requiring a shaft between the turbine blade and the compressor blade. The power produced by each turbine blade is consumed by its own joined compressor. The disc turbocharger has a multi-disc engine that works as a multi-stage turbocharger with a smaller size and no piping between the turbochargers. The disc turbocharger uses a waste spool valve for control of the.

A rotor for a large-diameter axial ventilator for industrial use. The rotor includes a hub and n blades, where each rotor blade includes a root portion for the structural connection to the hub and an aerodynamic portion; the rotor further includes a coaxial accessory axial fan including n radially extending vanes which, in an axial view, is substantially included within the region P defined by the n radially inner ends of the aerodynamic portions of the rotor blades. The embodiments further relates to a large-diameter axial ventilator for industrial use including such a rotor.

A low-pressure compressor for a turbine engine, such as an aircraft turbojet engine includes a rotor with two rows of rotor blades between which two annular ribs are positioned; and one annular row of stator blades between the rotor blades. An internal shroud is connected to the stator blades. The internal shroud includes abradable material collaborating with the annular ribs, and annular teeth made of an abradable material and which extend radially towards the rotor, so as to provide sealing. The system may be used in a method for manufacturing a bypass turbojet engine compressor.

A housing device for a compressor stage of a compressor device of an aircraft engine that is embodied in a multi-stage design, including a flange area for connection to at least one housing device of another compressor stage that is adjacent in the axial direction. The housing device has a rotor area that during operation of the housing device directly acts together with the rotor blades of a rotor device in the radial direction of the compressor device. Further, the housing device has at least one reception area that is provided for receiving guide blades of a stator device. At least one part of the housing device is made of a sheet metal part. What is further described is a method for manufacturing such a housing device, with at least one part of the housing device being manufactured by means of a forming process.

A vertical pump features stationary bowl assembly, a rotating power transmission shaft, impellers and bottom wear-ring bearings. The stationary bowl assembly includes bowls, each bowl having a respective bowl bottom inside surface. The rotating power transmission shaft is configured to extend through the stationary bowl assembly. The impellers are arranged on the rotating power transmission shaft to rotate and draw material through the stationary bowl assembly, each impeller having a respective impeller bottom outside surface. Each bottom wear-ring bearing is arranged between the respective impeller bottom outside surface of each impeller and the respective bowl bottom inside surface of each bowl, made from a non-galling bearing material, and configured to maintain the alignment of the rotating power transmission shaft in relation to the stationary bowl assembly.