A turbine abradable component includes a support surface and a thermally sprayed ceramic/metallic abradable substrate coupled to the support surface for orientation proximal a rotating turbine blade tip circumferential swept path. An elongated pixelated major planform pattern (PMPP) of a plurality of discontinuous micro surface features (MSF) project from the substrate surface. The PMPP repeats radially along the swept path in the blade tip rotational direction, for selectively directing airflow between the blade tip and the substrate surface. Each MSF is defined by a pair of first opposed lateral walls defining a width, length and height that occupy a volume envelope of 1-12 cubic millimeters. The PMPP arrays of MSFs provide airflow control of hot gasses in the gap between the abradable surface and the blade tip with smaller potential rubbing surface area than solid projecting ribs with similar planform profiles.

The invention relates to a clamping system (1) comprising a clamping jaw (7) mounted on the shaft of a pneumatic or hydraulic cylinder (4), wherein said cylinder has a structure which drives the clamping jaw towards its clamping position when the pneumatic or hydraulic energy supply of the cylinder is interrupted, the pneumatic or hydraulic energy supply of the cylinder opposing the clamping, and where means (8) are provided for locking the cylinder when the clamping jaw is in a non-clamped position.

A hydrophilic surface pattern on a removal surface of a steam turbine directs surface moisture in at least one predetermined direction to enhance moisture management by enhancing moisture removal or otherwise reducing erosion caused by moisture in the steam turbine. In some embodiments, the removal surface is located on the outer surface of the nozzle wall adjacent an extraction opening. In some embodiments, the removal surface is located on the surface of the bucket and directs moisture toward the turbine rotor. In some embodiments, the removal surface is located on the surface of the turbine casing or the surface of the nozzle and directs moisture toward a drain in the turbine casing. The hydrophilic surface pattern is preferably laser-etched as a nano-scale pattern to create the hydrophilic surface. In some embodiments, the hydrophilic surface pattern creates a superhydrophilic surface.

A turbine component having a face-centered cubic ferromagnetic damping coating with high damping loss attributes applied in a non-molten solid state.

A nacelle exhaust nozzle having a deployable noise-reducing component is described. The noise-reducing component includes an annular perforated sleeve coinciding with the inner nacelle loft line and circumscribing a mixed exhaust gas flow exiting the nacelle. The annular perforated sleeve is radially spaced apart from of a displaceable wall of an inflatable envelope that is displaceable between a deployed position, wherein noise-reduction is active, and a retracted position, wherein noise-reduction is inactive. When the inflatable envelope is pressurized, portions of the displaceable wall project through openings in the perforated sleeve and into the exhaust gas flow to form a rough surface at the loft line which causes a reduction in noise level. The portions of the displaceable wall that project through the openings in the perforated sleeve when the inflatable enveloped is pressurized include a plurality of dimples formed on the inner wall and forming the rough surface.

A mechanical part for an aircraft turbomachine is made of metal and includes at least one profiled surface configured to ensure an oil flow during operation. The surface has a hydrophobic and/or lipophobic coating or a surface texturing rendering the surface hydrophobic and/or lipophobic.

A seal system a ceramic component having a surface region defining a first surface roughness, a metallic component situated adjacent the surface region, and a coating system disposed on the surface region. The coating system includes a silicon-containing layer on the surface region and a barrier layer on the silicon-containing layer. The silicon-containing layer has a surface in contact with the barrier layer. The barrier layer has a surface in contact with the metallic component. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The barrier layer limits interaction between silicon of the silicon-containing layer and elements of the metallic component. The barrier layer has a coefficient of thermal expansion that is within about 60% of a coefficient of thermal expansion of the ceramic component. A gas turbine engine and a method are also disclosed.

A turbocharger for an internal combustion engine includes a rotating assembly having a turbine wheel disposed inside a turbine housing and a compressor wheel disposed inside a compressor cover. The turbocharger also includes a waste-gate assembly configured to selectively redirect at least a portion of the engine's post-combustion gases away from the turbine wheel. The waste-gate assembly includes a valve, a rotatable shaft connected to the valve, and a bushing fixed relative to the turbine housing and disposed concentrically around the shaft such that the shaft rotates inside the bushing for opening and closing the valve. The bushing is defined by a length, an outer surface in contact with the turbine housing, and an inner surface in contact with the shaft. The inner surface includes a plurality of longitudinal grooves configured to counteract friction between the bushing and the shaft and avoid seizure of the shaft relative to the bushing.

A fixture assembly includes a frame with a tip rail displaced from a main body. A method of polishing a gas turbine engine component includes restricting a flow of media adjacent to a tip of a component with an airfoil to be generally equal to a flow of media adjacent to a sidewall of the airfoil.

An example turbocharger includes a turbine blade wheel, a housing including a flow path through which gas received from an inlet flows, and a variable capacity assembly disposed in the housing and configured to receive the gas from the flow path and guide the gas to the turbine blade wheel. The housing includes a housing contact surface that is in contact with the variable capacity assembly in an axial direction of a rotation axis of the turbine blade wheel. The variable capacity assembly includes an assembly contact surface that is in contact with the housing contact surface in the axial direction. At least one of the housing contact surface and the assembly contact surface includes a high friction surface.