A disclosed system includes an impeller for a ventilator. The impeller includes a hub or hub ring configured to rotate about an axis and a plurality of vanes attached to the hub or hub ring. Each vane of the impeller has a leading edge facing a pressure side of the ventilator along the axis, and a trailing edge facing a suction side of the ventilator along the axis. The leading edge of each vane has a corrugated shape characterized by a first wavelength and the trailing edge has a corrugated shape characterized by a second wavelength, with the first wavelength being longer than the second wavelength. The impeller may further include injection molded plastic, die-cast aluminum, stamped sheet metal, or laser cut sheet metal that is embossed. The impeller may further be assembled from separately manufactured pieces that are secured to one another using joining, welding, or by interlocking tabs.

The present invention relates to a ventilator, aiming easier cleanup even in the position mounted on the ceiling or wall. According to the present invention, a ventilator may comprise an outer casing having a mounting space in an inside thereof, an inner casing mounted in the mounting space of the outer casing, a blowing fan received in an inner space of the inner casing, and a motor rotating the blowing fan, wherein a wave-shaped flow path is formed on each inner wall surface of the inner casing.

An impingement cooled component includes a first wall having a plurality of impingement holes and a second wall spaced apart from the first wall. The second wall is downstream of the first wall, relative to a cooling flow, the second wall has a contoured surface facing the first wall. The contoured surface includes a plurality of contours defined by at least one of a plurality of peaks and a plurality of valleys, and at least one of the contours in the plurality of contours is aligned with an axis defined by one of the impingement holes in the plurality of impingement holes.

An assembly forming an acoustic insulator having a first sheet, a pierced second sheet, and a plurality of first and second structures. Each first structure comprises a first and a second strip, wherein each is shaped to form half of the wall of a cage and wherein, for two successive halves, each strip comprises a facet of a joining wall. Each second structure is made up of a first and a second strip, wherein each is shaped to form half of the wall of a cone, wherein. For each strip, at least one of the wall halves of each cone is pierced. For two successive halves, each strip comprises one facet of the connecting wall. Each cone is located in a cell and each connecting wall is located between the two facets of a joining wall, and, between two adjacent first structures, a second structure is likewise fitted.

An impingement cooled component includes a first wall having a plurality of impingement holes and a second wall spaced apart from the first wall. The second wall is downstream of the first wall, relative to a cooling flow, the second wall has a contoured surface facing the first wall. The contoured surface includes a plurality of contours defined by at least one of a plurality of peaks and a plurality of valleys, and at least one of the contours in the plurality of contours is aligned with an axis defined by one of the impingement holes in the plurality of impingement holes.

A variable turbine geometry (VTG) turbocharger is disclosed. The VTG turbocharger may comprise a turbine section, a bearing section, and an actuation pivot shaft (APS) having a bearing side in the bearing section and a pressure side in the turbine section. The VTG turbocharger may further comprise a bushing surrounding the APS and extending from a first end at the pressure side to a second end at the bearing side. In addition, the VTG turbocharger may further comprise a face seal assembly including a cup spring and a composite ring seal circumscribing the APS at the pressure side, with the cup spring forming a face seal with the first end of the bushing. The face seal assembly may further include a spring circumscribing the APS at the bearing side and engaging the second end of the bushing.

A stage for a compressor or a turbine in a turbine engine can include an annular row of airfoils radially extending from corresponding platforms, where each platform can include a fore edge and aft edge and each airfoil can include a leading edge and trailing edge. At least one of the platforms can have a scalloped flow surface including a bulge and a trough.

The present invention provides a seal assembly for use in a centrifugal compressor and a centrifugal compressor having same. The centrifugal compressor comprises an impeller and a housing, wherein the impeller comprises a gimbal, provided on the back of the impeller, having an inner diameter and an outer diameter; and the seal assembly for use in a centrifugal compressor comprises a sealing section, the sealing section comprising a sealing tooth formed on the impeller and a sealing ring provided on the housing, wherein an elastic part is provided on a contact surface of the sealing ring with the sealing tooth. According to the seal assembly of the present invention, the sealing clearance between the sealing ring and the sealing tooth is effectively reduced by way of multiple sets of sealing sections and the elastic parts provided therebetween.

An engine component for a gas turbine engine generating hot combustion gas flow is provided. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component also includes a flow conditioning structure provided upstream of the outlet on the hot surface. The flow conditioning structure can include a ridge extending from the hot surface.

A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, an annular ring configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a first O-ring disposed between the annular ring and the fluid transfer tube, a second O-ring disposed between the base member and the annular ring, and an attachment ring configured to secure the annular ring and the base member to the casing.