The invention relates to a fan housing (1), a fan and an operating system having a fan. The fan housing (1) has a volute shape and includes a volute tongue (2) and a cavity (16) between an air inlet and an air outlet, the volute tongue is provided with a protrusion (20) configured to extend in a direction substantially parallel to an axial direction of an impeller mounted in the cavity and has at least one peak (24) in a longitudinal section of the fan housing, and the peak is opposed to an annular projection (32) located at the circumferential outer surface of the impeller. The use of the invention can effectively reduce the noise level during the operation of the fan and improve fan performance, thereby considerably improving users' comfort and satisfaction.

A fuel distribution device is provided wherein an axis is defined. The device comprises a body housing a distribution path for fuel; the distribution path has one inlet and a plurality of outlets; the inlet is located on the external surface of the body at an end of an inlet branch of the distribution path; the plurality of outlets are located on the external surface of the body at ends of a corresponding plurality of outlet branches of the distribution path; the inlet branch and the outlet branches are fluidly connected to a distribution space; and the outlet branches are arranged radially.

A rotor assembly comprises a rotor having annular flange including a plurality of protrusions axisymmetrically disposed about the annular flange, each protrusion having a mounting aperture for selectively receiving a balancing feature, and a plurality of slots axisymmetrically disposed about the circumference of the annular flange between adjacent protrusions. Each slot has a pair of converging flat portions extending axially inwardly from an adjacent protrusion end, an inner flat portion at an inner end of each slot, and a pair of curved portions respectively joining each converging flat portion to the inner flat portion in each slot. Each slot has a depth at least as great as an adjacent mounting aperture depth extending normally from the adjacent protrusion end to a far end of the corresponding mounting aperture.

A turbine operable to produce a flow of exhaust gas along a central axis includes a strut having a flow portion positioned within the flow of exhaust gas and a strut cover having a length and positioned to surround the flow portion of the strut, the strut cover including a leading-edge portion, a mid-chord portion, and a trailing-edge portion. The mid-chord portion has a uniform cross-section, and the trailing-edge portion has a trailing-edge center positioned such that the mid-chord portion and the trailing-edge portion define a master chord plane. The leading-edge portion defines a leading-edge nose, and the leading-edge portion is twisted with respect to the master chord plane and the leading-edge nose along the length defines a curve that is not coincident with the master chord plane.

A radial impeller includes a hub, a disk, and a plurality of blades. The disk is affixed to the hub. The disk has a disk plane defined by the disk. Each blade of the plurality of blades is affixed to the disk. Each blade includes a “C” shaped body portion and an upper and lower horizontal extension. The upper horizontal extension extends along an upper plane parallel to the disk plane. The lower horizontal extension extends along a lower plane parallel to the disk plane.

A nested lattice structure for use in a damping system for a turbine blade includes a first lattice structure including: a first outer passage including a hollow interior; a second outer passage including a hollow interior; and an outer node including a hollow interior and forming an intersection of the first outer passage and the second outer passage. The nested lattice structure includes a second lattice structure nested within the hollow interior of the first lattice structure. The second lattice structure includes: a first inner passage; a second inner passage; and an inner node forming an intersection of the first inner passage and the second inner passage. Each of the first inner passage, the second inner passage, and the inner node are nested within the respective first outer passage, the second outer passage, and the outer node.

A sealing structure for a gas turbine engine includes a rotor that has a rim with slots and a cooling passage. The rotor is rotatable about an axis. First and second blades are arranged in the slots and respectively including first and second shelves facing one another within a pocket that is in fluid communication with the cooling passage. The first and second shelves form an opening. A reversible seal is arranged within the pocket and has a body that is configured for operative association with the first and second blades in any of four orientations to seal the opening in a second condition. The seal includes first and second protrusions respectively extending from first and second faces opposing one another. The first protrusions supported on the rim in a first condition.

An internally cooled component of a gas turbine engine is provided. The component may include a cooling passage at least partially defined by a first wall and a second wall with a first pedestal extending from the first wall to the second wall. The first pedestal may have a chevron geometry. A second pedestal may extend from the first wall to the second wall and also have a chevron geometry. A gap may be defined by the first pedestal and the second pedestal with the gap oriented between the first pedestal and the second pedestal.

An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with a metering portion with a constant cross-sectional area and a cross-sectional shape having a maximum height that is offset relative to a longitudinal centerline of the metering portion; and a diffuser portion extending from the metering portion to the external surface of the body.

A housing element (12) for an intermediate turbine housing of a gas turbine, in particular an aircraft gas turbine; the housing element (12) being installable or installed in the intermediate turbine housing radially outwardly, in each case between a plurality of circumferentially spaced struts; the housing element (12) having a planar form and, relative to the radial outer side (16) thereof, a plurality of depressions (18c), is provided. On the radial inner side (32, 34) thereof, the housing element (12) has at least one recess (26) that is configured outside of the regions in which depressions (18c) are formed on the radial outer side (16).