Abstract: A turbine rotor blade arrangement for a gas turbine, having a turbine disc and a turbine rotor blade ring that comprises a plurality of rotor blades. The turbine disc has disc channels for providing air, wherein a disc channel respectively ends in a discharge hole in the area of a blade root reception area. The rotor blades have cooling air channels for cooling the rotor blades. In the blade root or between the blade root and the blade root reception area, an air channel is formed via which sealing air is discharged that is fed in from the disc channel. It is provided that the blade root comprises a deflection device that is provided and is configured for the purpose of partially deflecting air exiting the disc channel in the direction of the air channel. Another embodiment of the invention relates to a method for the provision of sealing air in a turbine rotor blade arrangement.

Abstract: An impeller for use in an aquarium filter pump includes a shaft and a plurality of impeller blades radially extending from the shaft. Each of the impeller blades includes opposite blade faces. A depression is in each of the blade faces and aids in pushing the water. The depression can be a variety of shapes and can have its deepest portion along one of the edges of the blade.

Abstract: An adjustment device for adjusting several guide vanes of the engine, wherein the adjustment device includes at least one adjusting element that couples with the guide vanes and is mounted in an adjustable manner, a connection element that couples with the adjusting element, as well as a crank shaft for controlling an adjusting movement of the adjusting element, and the crank shaft has at least one coupling element which couples with the connection element and at which the connection element is hinged to transform a rotational movement of the crank shaft about a longitudinal axis of the crank shaft into an adjusting movement of the adjusting element for adjusting the guide vanes. The crank shaft has a modular design with at least two shaft modules that are arranged behind each other along the longitudinal axis of the crank shaft.

Abstract: An airfoil for a gas turbine engine includes a cavity including an internal surface of an outer wall. A baffle is disposed within the cavity and spaced apart from the internal surface. A partition is disposed between the baffle and the internal surface to divide a space between the baffle and the internal surface into at least a first passage and a second passage. A gas turbine engine is also disclosed.

Abstract: A turbine of an organic Ranking cycle (ORC) is described. The turbine includes a shaft supported by at least two bearings and a plurality of axial stages of expansion, defined by arrays of stator blades alternated with arrays or rotor blades. The rotor blades are sustained by corresponding supporting disks. A main supporting disk is directly coupled to the shaft in an outer position with respect to the bearings, and the remaining supporting disks are constrained to the main supporting disk, and one to the other in succession, but not directly to the shaft. Some of the remaining supporting disks are constrained to the main supporting disk and cantileverly extend from the same side of the bearings that support the shaft, so that the center of gravity of the rotor part of the turbine is shifted more towards the bearings.

Abstract: A centrifugal compressor includes a rotation shaft, an impeller, a housing including a first chamber, a second chamber of which pressure is lower than the first chamber, and a partition wall that partitions the first chamber and the second chamber and includes a through hole through which the rotation shaft is inserted, and a seal member arranged in the housing. The seal member includes a gas seal and a support. When the rotation shaft is rotating, the gas seal surrounds an outer circumferential surface of the rotation shaft in a non-contact state in which dynamic pressure forms a gap between the gas seal and the outer circumferential surface of the rotation shaft. The support supports the gas seal in a state in which the gas seal is movable in a direction intersecting an axial direction of the rotation shaft.

Abstract: The example embodiments are directed to a heat dissipation system for an electric aircraft engine. In an example, the aircraft engine includes an electric system configured to power an engine fan to provide thrust to an aircraft, the electric system including cooling channels to receive a coolant to cool one or more components of the electric system, a power source to power the electric system, and one or more guide vanes connected to the cooling channels of the electric system and configured to receive the coolant heated by and output from the cooling channels, wherein the one or more guide vanes are further to cool the heated coolant and transfer the cooled coolant back to the cooling channels of the electric system. By dissipating heat from electric system via the guide vanes, the cooling system can provide sufficient cooling without adding additional drag to the aircraft.

Abstract: A cut-back of a blade or vane in a gas turbine may comprise a first sidewall; a plurality of trailing ribs extended from the first sidewall and arranged along an end of the first sidewall; a second sidewall separated from the first sidewall, having a longer tail than the first sidewall and in contact with the plurality of trailing ribs; and one or more cut-back blocks extended between two trailing ribs along the inner surface of the second sidewall. The cut-back of the blade or vane may reduce the weight through the trailing ribs and the cut-back blocks formed at the trailing edge, and improve a heat transfer effect while retarding crack growth.