An air cooled component for a gas turbine engine including a first wall and a second wall having opposing inner surfaces to define a gap therebetween, and a lattice of intersecting elongate ribs extending longitudinally along the first and second walls and transversely between the inner surfaces of the first and second walls to provide a plurality of cells. One or more portions of the ribs include an aperture to provide a flow path between adjacent cells so that the cells are in fluid communication.

A fluid passage assembly and method for manufacturing a fluid passage assembly for a power generator. The fluid passage assembly includes a manifold body having an inlet conduit for receiving a fluid, and at least one distribution conduit fluidly coupled to the inlet conduit for dispensing the fluid to cool the power generator, wherein a cross-section of the at least one distribution conduit is includes at least one corner.

A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body comprises a ceramic material. A shape of the extension comprises a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis comprises an ellipse. The extension is connected to the investment core body by the connection portion.

An engine component assembly for impingement cooling. The engine component assembly includes an engine first component having a cooled surface. The engine first component having a flow path on one side of the cooled surface. A second component is a disposed adjacent to the engine first component between the flow path and the engine first component, and has a plurality of openings forming an array through the second component. The cooling flow path passes through the plurality of openings to cool the cooled surface. The second component having a surface facing the cooled surface of the engine first component. A plurality of discrete cooling features that have at least one wall that has a curved cross-section extend from the second component surface into a gap between and toward the cooled surface of the engine first component and defining an array.

A propeller shaft assembly for an aircraft engine includes a shaft having a bore extending through the shaft at a front end thereof, the front end of the shaft having an outer surface facing radially outwardly from the shaft and an inner surface spaced apart from the outer surface and facing radially inwardly to the bore. The shaft has a front flange extending radially outwardly on the outer surface, the front flange having a base merging with the outer surface of the shaft. A sleeve is coupled to the shaft within the bore by an interference fit between the sleeve and the shaft, at least part of the sleeve axially aligned with the front flange. The sleeve axially extends from a front to a rear sleeve end, the rear sleeve end axially offset from the engine side surface of the front flange at the base of the front flange.

In an embodiment, a blower for a heating, ventilation, and air conditioning system includes a blower wheel and a housing. The blower wheel includes backward-curved blades configured to rotate in a rotational plane. The housing forms an at least hexagonal cross-section around at least a portion of the rotational plane, where the blower wheel is positioned within the housing such that there exists a first distance and a second distance. The first distance is measured radially outward from a center of the blower wheel to a first side of the at least hexagonal cross-section. The second distance is measured radially outward from the center of the blower wheel to a second side of the at least hexagonal cross-section. The second distance forms a an acute angle with the first distance. The first distance and the second distance are unequal and less than a diameter of the blower wheel.

In an embodiment, a blower for a heating, ventilation, and air conditioning system includes a blower wheel and a housing. The blower wheel includes backward-curved blades configured to rotate in a rotational plane. The housing forms an at least hexagonal cross-section around at least a portion of the rotational plane, where the blower wheel is positioned within the housing such that there exists a first distance and a second distance. The first distance is measured radially outward from a center of the blower wheel to a first side of the at least hexagonal cross-section. The second distance is measured radially outward from the center of the blower wheel to a second side of the at least hexagonal cross-section. The second distance forms a an acute angle with the first distance. The first distance and the second distance are unequal and less than a diameter of the blower wheel.

A sealing element for a turbomachine, in particular an aircraft engine, with a housing for the at least one rotating structural component is provided. The sealing element comprises a honeycomb structure for arrangement inside the housing, wherein the honeycomb structure extends in a first direction, wherein support structures are connected to the honeycomb structure in one piece and/or in a pattern-like manner and extend at least partially into the honeycomb structure, and the support structures extend at least partially or completely in a second direction that is different from the first direction. The support structures have planar portions, which are formed by at least one partially or completely closed cell together with the honeycomb structure.

In a rotary machine, platforms are each in a shape of a flat surface extending in an axial line direction and each includes damper abutting surfaces extending to be close to each other as approaching the outer side in the radial direction while opposing each other in the peripheral direction in each of the platforms adjacent to each other, and the damper pin forms a regular polygonal prism extending in the axial line direction and includes a damper pin main body in which an angle formed by two side surfaces among a plurality of side surfaces corresponds to an angle formed by the damper abutting surfaces adjacent to each other.

A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.