A device for cooling a component to be cooled of a gas turbine/turbo machine having a hot-gas-impinged outer surface, a target surface of the component, and an integrated cooling passage, includes: an impingement cooling element arranged within the cooling passage, the impingement cooling element having plural impingement cooling bores; and a surface structure arranged on the target surface. The impingement cooling element is spaced apart from the target surface of the component and configured so as to conduct a cooling fluid as an impingement cooling jet is onto the target surface, such that the impingement cooling jet impinges on the surface structure.

A diffuser is proposed which is formed as the gap between rotationally-symmetric surfaces which face each other. Moving in the radial direction, the axial extent of the gap generally decreases to a minimum value in a throat portion of the diffuser, and then generally increases again. The distance from the rotational axis of the compressor to the throat may be approximately at least 125% of the radius of the compressor wheel. The inventors have found that a throat at this distance from the rotational axis may lead to higher efficiency at high flow rates, especially for relatively low turbo speeds. This is because the spacing between the compressor wheel and the throat permits diffusion of the gas streams leaving the compressor wheel.

A gas turbine hot part includes: a body portion; a porous portion forming at least a part of the body portion or disposed on at least a part of the body portion and allowing a cooling gas to pass therethrough; and at least one filter disposed upstream of the porous portion in a flow direction of the cooling gas and capable of trapping foreign substances that cannot pass through the porous portion.

Rotor blades and turbomachines are provided. A rotor blade includes a platform and an airfoil extending radially from a root proximate the platform to a tip. The airfoil includes a leading edge and a trailing edge. The airfoil further includes a pressure side surface extending between the leading edge and the trailing edge. The airfoil also includes a suction side surface disposed opposite the pressure side surface and extending between the leading edge and the trailing edge. The leading edge, the trailing edge, the pressure side surface, and the suction side surface collectively define a first profile at the tip and a second profile radially inward from the tip. The first profile includes a suction side overhang, a pressure side overhang, and a pressure side underhang relative to the second profile.

A supply duct of a compressor of a turbine engine, formed from internal and external walls of revolution around an axis and opposite one another to define a circulation stream of a fluid, is provided. The stream allows the fluid to be routed from the inlet of the duct to the inlet of the compressor. The radius of the external wall at the inlet of the duct is greater than the radius of the duct at the inlet of the compressor. The duct includes a portion for which the radius of the external wall along the portion is less than the radius of the external wall at the inlet of the compressor, and the radius of the internal wall along the portion of the duct is less than the radius of the internal wall at the inlet of the compressor.

A nacelle assembly of a gas turbine engine includes an annular structure defining a central axis, and having a radially inward surface and a radially outward surface, the radially inward surface at least partially defining a bypass duct. An aft portion of the radially inward surface at least partially defines an axially extending convergent-divergent exit nozzle. A secondary nozzle flap is radially spaced from the aft portion of the radially inward surface. The secondary nozzle flap and the aft portion of the radially inward surface define a secondary bypass duct therebetween. The secondary nozzle flap is operably connected to the annular structure such that the secondary nozzle flap is selectably movable relative to the aft portion of the radially inward surface, thereby changing a cross-sectional area of a secondary bypass duct exit.

An exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, and exactly one strut connecting the centerbody to the nozzle wall. The strut is connected to the nozzle wall by means of a connecting structure that is displaceable in the axial direction of the outer nozzle wall. At least one actuator is provided interacting with the connecting structure or the outer nozzle wall for displacing the strut in the axial direction.

An abradable sealing element comprises a substrate and a sealing structure. The sealing structure comprises one or more wall structures extending from the substrate and defining at least one open cell which is filled with abradable material. The one or more wall structures are formed by additive-layer, powder-fed, laser-weld deposition onto the substrate. The one or more wall structures are formed from nickel-based superalloy and constitute from about 10% to about 50% of the total volume of the sealing structure.

A bearing includes a thrust gas bearing attached to a journal bearing and two or more converging-diverging orifices defined in a surface of at least one of the thrust gas bearing and the journal bearing. The converging-diverging orifices supply at least one pressurized gas to an interior of the bearing. Hydrodynamic lifting grooves are provided on the faces of the thrust gas bearing and the journal bearing and provide improved load capacity and sealing capabilities. Control over the ratios of the pressurized gases provides for additional sealing capabilities and reduced leakage. A metal mesh damper provides increased damping of the gas bearing.

A blade vibration monitoring device includes: a rotary machine including a rotating shaft that extends along an axis, and a plurality of moving blades having moving blade bodies that extend radially outward in a radial direction from the rotating shaft, and shrouds that are provided at tips of the moving blade bodies and are in contact with each other in a circumferential direction; and a sensor that is provided on the outside of the shroud in the radial direction to face the shroud, and is configured to detect a change in an outer circumferential surface of the shroud, in which the outer circumferential surface of the shroud includes a first surface, and a second surface which is disposed to be interposed between the first surfaces from both sides in the circumferential direction, and in which a detection signal from the sensor is different from that of the first surface.