A tube gallery for a gas turbine engine includes a body. The body includes an external surface. The body also includes a plurality of channels defined in the body. Each channel includes an inlet disposed on the external surface, an outlet spaced apart from the inlet and disposed on the external surface, and a passage extending between and fluidly communicating the inlet to the outlet. The passage of each channel has a non-circular cross-sectional shape. The non-circular cross-sectional shape has a first maximum dimension along a first direction and a second maximum dimension along a second direction orthogonal to the first direction. The first maximum dimension is greater than the second maximum dimension by a factor of at least 1.2.

Devices, systems, and methods of manufacturing wind turbine root attachment are provided. In various embodiments, an assembly for wind turbine root attachments includes a bushing, a core, and a filler. The bushing includes a body having cutouts extending from the proximal end to the distal end on either side of the bushing and a core cutout at the distal end. The bushing further includes an ear disposed at the proximal end of the bushing and within the first cutout. The core includes two wedges where the thick end of each wedge abut one another. The thin end of the proximal wedge is disposed within the core cutout and the core includes cutouts extending from the proximal end to the distal end on either side of the core. The filler is disposed within the cutout on the side of the assembly having the ear.

An exhaust hood (Ec) of the present invention is provided with an inner casing (21), an outer casing (30), and a diffuser (26). The inner casing (21) surrounds a rotor from the outside in a radial direction, and forms a first space (21s) in which a fluid flows in an axial direction (Da) between the rotor and the inner casing (21). The diffuser (26) is provided with a bearing cone (29) that has a diameter that gradually widens moving towards an axial downstream side (Dad) and forms a cylindrical shape extending to the axial downstream side (Dad) to be continuous with the outer circumferential surface of a rotor shaft that forms the first space (21s). An end edge (29a) on the axial downstream side (Dad) of the bearing cone (29) forms an oval shape in which, in a direction orthogonal to an axial line (Ar), a distance (R2an) between the axial line (Ar) and a second cone end part (29ab) of a second side (Dan) is greater than a distance (R2ex) between the axial line (Ar) and a first cone end part (29aa) of a first side (Dex).

A blade including at least one web and a vane having a leading edge and a trailing edge, wherein, for at least one aerofoil of the vane in the vicinity of the web, a maximum sweep angle associated with a position along a chord of the aerofoil extending from the leading edge to the trailing edge of the vane corresponding to a relative chord length of at least 50%.

The present invention relates to a blade for a gas turbine, in particular of an aircraft engine, having a blade airfoil, which has a blade-root-side first profile section and a blade-tip-side second profile section, which is spaced apart from the first profile section in a radial direction, from the first profile section to the second profile section, by a blade airfoil height, wherein a stagger angle of the blade airfoil changes with a height in the radial direction over the first profile section at least over certain portions, wherein, in a first region between a first height and a second, greater height, the change in the stagger angle over the height does not decrease with increasing height at least over certain portions.

The present invention relates to a rotating blade for a turbomachine, having a blade element and a shroud, wherein the shroud is profiled at a peripheral side, i.e., when observed in a tangential section, has a contact flank that is oriented axially, at least proportionally, and has a free flank that is also oriented axially, at least proportionally, and is in fact opposite the contact flank, wherein, when observed in the tangential section, an intermediate segment between the contact flank and the free flank has a first curvature in a first transition segment to the contact flank and has a second curvature in a second transition segment to the free flank, wherein the first curvature is greater than the second curvature.

A centrifugal fan includes a housing and an impeller. The housing includes a sidewall, and the sidewall includes a tongue portion. The impeller includes a fan hub and a plurality of blades. The fan hub is rotatably disposed in the housing, and the tongue portion has an inner contour line on a reference plane. The blades connect to the fan hub. Each one of the blades has an end surface facing the sidewall. The end surface has an outer contour line on the section of the blade. Any two adjacent blades have different outer contour lines. The outer contour line of at least one first blade of the plurality of blades is parallel to the inner contour line. The outer contour line of at least one second blade of the plurality of blades is not parallel to the inner contour line.

A blower has a blower housing of clamshell construction, including two housing members having a scroll back wall molded with radial draft, an impeller and a motor within the housing, and a static tap connected to the housing. The impeller has a backplate with a backplate back surface region of substantially the same radially converging shape as that of a front surface region of the scroll back wall formed by the radial draft, providing a substantially uniform axial gap between the backplate back surface region and the scroll back wall. The impeller has a ring connected by a skirt to the back plate to define a stepped area behind the ring. The impeller includes impeller blades extending forwardly from the impeller backplate and the ring and back fins extending rearwardly from the ring. The blower has a scroll width of about twice an impeller exhaust width.

A turbine rotor blade according to at least one embodiment of the present invention is to be connected to a rotational shaft so as to be rotatable around an axis and includes: a hub having a hub surface inclined with respect to the axis in a cross-section along the axis; at least one rotor blade disposed on the hub surface; and a connection passage disposed inside the turbine rotor blade and connecting a first opening disposed in the at least one rotor blade and a second opening disposed downstream of the first opening in the turbine rotor blade.

A centrifugal fan includes: a fan, blades; and a scroll casing housing the fan, the scroll casing including a discharge portion, and a scroll portion including a side wall, a circumferential wall, and a tongue portion. In the circumferential wall, at a first end between the circumferential wall and the tongue portion, and at a second end between the circumferential wall and the discharge portion, a distance between an axis of the rotational shaft and the circumferential wall is equal to a distance between the axis of the rotational shaft and a standard circumferential wall, and is greater than or equal to the distance between the first end and the second end of the circumferential wall, the circumferential wall including a plurality of extended portions between the first end and the second end of the circumferential wall.