A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.

A side-channel compressor (1) for a fuel cell system (37) for conveying and/or compressing a gas, in particular hydrogen, having a housing (3), having a compressor chamber (30) which is situated in the housing (3) and which has two encircling side channels (19, 21), having a compressor impeller (2) which is situated in the housing (3) and which is arranged so as to be rotatable about an axis of rotation (4), wherein the compressor impeller (2) has conveying cells (28) arranged at the circumference thereof and in the region of the compressor chamber (30), and having in each case one gas inlet opening (14) formed on the housing (3) and one gas outlet opening (16), which openings are fluidically connected to one another via the compressor chamber (30), in particular the two side channels (19, 21), and wherein, in the region of the compressor chamber (30), an encapsulation of the respective side channel (19, 21) is realized by at least one separation region (35) by means of a surface pairing of the compressor wheel (2) and of the housing (3). According to the invention, here, the at least one separation region (35) is formed by a surface pairing of the components compressor impeller (2) and housing (3) such that the respective one component has encircling edges (5), in particular with encircling tips (11), and the respective other component has an encircling, at least approximately planar counterpart surface (23).

A feed-through assembly for a bulkhead for moving and static engine components. The feed-through assembly can be configured to include flexible convolutions that allow for movement and sealing of the engine component relative to the bulkhead. In one aspect, a flexible convoluted spherical element can be provided in the feed-through assembly. In another aspect, a flexible convoluted bellow element can be provided in the feed-through assembly. These flexible convoluted elements can have multiple convolution sections including convolution sections with varying stiffness. The convolution sections can be configured to allow movement of the shaft relative to the bulkhead, including, transverse deflection and tilt.

A blade includes an airfoil portion including a pressure surface and a suction surface each extending between a leading edge and a trailing edge along a spanwise direction, and at least one communication hole extending m the airfoil portion and having a first and a second opening end opening to the pressure and suction surface, respectively. The first opening end is located on a first cross-section perpendicular to the spanwise direction at a first position in the spanwise direction, the second opening end is located on a second cross-section perpendicular to the spanwise direction at a second position in the spanwise direction, and a dimensionless blade chord length position of the first opening end with respect to the leading edge on the first cross-section is larger than a dimensionless blade chord length position of the second opening end with respect to the leading edge on the second cross-section.

A three-dimensional auxetic structure, comprising a plurality of adjoining hollow cells, each hollow cell having cell walls and a transversal cross section of the plurality hollow cells following a two-dimensional auxetic pattern, each cell wall comprising folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are defined in the cell walls and the cell walls being foldable along the folding lines.

A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.

A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of vanes. The first rotor disk is configured to rotate about a rotational axis. The first rotor disk is configured from or otherwise includes disk material. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The vanes are arranged circumferentially around the rotational axis and axially between the first rotor disk and the second rotor disk. The vanes include a first vane, which first vane is configured from or otherwise includes vane material that is different than the disk material.

A method for joining two structural elements by welding, in particular by butt welding comprises forming a weld line joining the two structural elements; and adding material across the weld line, thereby forming one or more crack stoppers for limiting crack propagation along the weld line. The one or more crack stoppers each have a limited extension along the weld line as seen in relation to a length of the weld line. A structural system comprising two structural elements joined by the method is disclosed. The method may be applied, e.g., to components of aircraft engines.

A centrifugal compressor includes an impeller rotatably disposed and having a plurality of first blades and a shroud cover disposed on a leading edge side of the first blades partially in a rotational axis direction of the impeller and connecting the first blades circumferentially adjacent to each other. The shroud cover is shaped such that a position of at least one of an upstream edge or a downstream edge of the shroud cover in the rotational axis direction changes along a circumferential direction of the shroud cover.

A containment structure for a rotor includes a shroud and a shroud reinforcement. The shroud is coaxial with and partially surrounds the rotor and includes a tubular section, a transition section, and a flange section. The tubular section extends axially past a first side of the rotor. The transition section connects to the tubular section and is adjacent to a curved side of the rotor. The flange section connects to the transition section opposite the tubular section. The flange section extends radially past a radially outer side of the rotor. The shroud reinforcement is connected to a radially outer surface of the transition section. The shroud reinforcement encloses the transition section and includes a support scaffold and a reinforcing material. The support scaffold includes a series of geometric retaining features encircling a radially outer surface of the transition section. The reinforcing material couples to the support scaffold and restricts shroud radial expansion.