Abstract:
This disclosure relates to a gas turbine engine. The engine includes a component having a first wall and a second wall spaced-apart from the first wall. The component further includes a cooling passageway provided in part by a helical wall between the first wall and the second wall.
Abstract:
A gas turbine engine airfoil includes an airfoil structure including an exterior surface that is provided by an exterior wall that has a leading edge. A radially extending interior wall within the airfoil structure separates first and second radial cooling passages. The first cooling passage is arranged near the leading edge. A radially extending trench is in the leading edge. An impingement hole is provided in the interior wall and is configured to direct a cooling fluid from the second cooling passage to the first cooling passage and onto the exterior wall at the leading edge.
Abstract:
A workpiece manufactured from an additive manufacturing system (AMS) having a particle separator and a method of operating includes modeling the workpiece into layers and modeling the layers into a plurality of regions. The AMS then deposits one of a plurality of particle types into a respective one of the plurality of regions. In this way, the surface finishes of the component may be controlled and material densities from one region to the next and from one layer to the next are also controlled.
Abstract:
A method of additively manufacturing is used to produce a component with an internal cooling channel for conveying a fluid. Powders in a powder bed are selectively fused to form a shaped layer of a body of the cooled component. The fusing is repeated on a layer-by-layer basis to form the body of the component with the internal cooling channel extending within the body, so that a peripheral wall of the internal cooling channel has a geometry that allows the peripheral wall to be self-supporting.
Abstract:
A seal for sealing a space defined by first and second components, the seal including at least one first seal and at least one second seal wherein at least a portion of the at least one first seal is disposed in the at least one second seal.
Abstract:
A component according to an exemplary aspect of the present disclosure includes, among other things, a body, a wall extending inside of the body and a plurality of vortex promoting features arranged in a helical pattern along the wall.
Abstract:
This disclosure relates to a gas turbine engine. The engine includes a component having a first wall and a second wall spaced-apart from the first wall. The component further includes a cooling passageway provided in part by a helical wall between the first wall and the second wall.
Abstract:
An additive manufacturing system utilizing an epitaxy process, and method of manufacture, utilizes a heating source and a cooling source to control thermal gradients and a solidification rate of each slice of a workpiece manufactured from a seed having a directional grain microstructure. An energy gun is utilized to melt selected regions of each successive layer of a plurality layers of a powder in a powder bed to successively form each solidified slice of the workpiece.