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.

The invention is related to the gas turbine stators of the gas turbine engines applied in aviation. The gas turbine stator, in the outer housing of which sectors of the split honeycomb ring (made as double-layer one) are installed with support elements on the front and rear axial ends of the sector. In this invention, the layer of the sector facing the outer housing is made U-shaped in the plane, the support elements are made as separate rotary bodies distributed uniformly along the circumference and the front support elements (on the gas flow direction) are larger than rear ones in terms of geometrical dimensions by factor 1.1 . . . 1.5. Therefore, the implementation of the invention proposed with the characteristic features above, in conjunction with the known features of the invention claimed enables reduction of the gas turbine stator weight and improvement its reliability without compromising the turbine efficiency.

A vibration damping system for a turbine nozzle or blade includes a body opening extending through a body of the turbine nozzle or blade between a tip end and a base end thereof. Elongated vibration damping element is disposed in the body opening and includes an elongated body having a first, free end and a second end fixed relative to one of the base end and the tip end. At least one wire mesh member surrounds the elongated body. The wire mesh member(s) frictionally engage with an inner surface of the body opening to damp vibration. A related method is also disclosed.

A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.

A turbocharger includes a variable nozzle disposed between a turbine housing and a bearing housing and a spring having an annular shape. The spring is disposed between the variable nozzle and the bearing housing, and is configured to generate a biasing force that biases the variable nozzle away from the bearing housing to widen a spacing between the variable nozzle and the bearing housing in a rotation axis direction. The spring includes an outer peripheral portion that applies the biasing force to the variable nozzle and an inner peripheral portion that comes into contact with the bearing housing. The outer peripheral portion of the spring is located further away from the turbine housing than the inner peripheral portion of the spring in the rotation axis direction.

A bearing assembly for a turbo-engine with a bearing and parts of a bearing temperature detecting device. The bearing includes a main body having a thermoplastic bearing layer. A space is defined in the interior of the main body and of the thermoplastic bearing layer for accommodating parts of the bearing temperature detecting device. The space has a through hole having a first opening in the thermoplastic bearing layer and a second opening located in the main body. The parts include a temperature conducting element, a temperature sensor, and a securing fixture that attaches the temperature conducting element. The first opening of the through hole has a chamfer and the first end of temperature conducting element has a head which is correspondingly shaped to the chamfer in a form fitting manner. The center-axis of the temperature sensor extends transversely to the center-axis of the temperature conducting element.

The invention relates to an assembly for a turbomachine with a longitudinal axis comprising a first annular wall (24), panels (38) being arranged around the longitudinal axis (A) and extending radially opposite said first annular wall (24) so as to form a flow surface for a flow of air, each panel (38) being secured to the first annular wall (24) by at least one fixing member (72) passing through an orifice in the panel (38) and secured to the first annular wall (24) by means of a sleeve and a stud forming a spacer.

Provided is a labyrinth seal including a first structure; and a second structure opposing the first structure. The first structure includes seal fins located at intervals in an axial direction and extending toward the second structure; a downstream wall surface located most downstream one of the seal fins and extending toward the second structure. A tip of the downstream wall surface located at a side of a tip of the most downstream seal fin, the side being close to the second structure in a radial direction and having a first outlet surface extending from the tip of the downstream wall surface toward a downstream side. The second structure includes a second outlet surface opposing the first outlet surface, a radial gap between the first outlet surface and the second outlet surface; and a cavity surface located upstream of the second outlet surface recessed away from the first structure.

A mold for manufacturing a turbomachine fan casing of composite material, includes a mandrel around which a fibrous preform of the fan casing is to be wound; counter-mold angular sectors assembled on the external contour of the mandrel which are intended to close the mold and to compact the fibrous preform wound on the mandrel; wherein each angular sector includes a first lateral flange positioned at the first end of the angular sectors and a second lateral flange positioned at a second end of the angular sectors, the first and second lateral flanges cooperating respectively with the second and first lateral flanges of the adjacent angular sectors. An angular sector includes a first groove formed in the first of second lateral flange, a first seal being positioned in the first groove, the first seal to be compressed between the first and second lateral flanges of two adjacent angular sectors.

An airfoil assembly for a gas turbine engine is disclosed and includes a platform portion defining a portion of a gas flow path and a root portion for attachment of the turbine airfoil, the root portion including a bottom surface including a bottom area and a plurality of inlets that define a total inlet area as a ratio of the inlet area to the bottom area. An airfoil extends from the platform and including a plurality of cooling air passages in communication with the plurality of inlets.