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: An airfoil has an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure. A swirl structure is operatively associated with the cooling passage and configured to impart a tangential velocity to the cooling medium flowing through the cooling passage. An airfoil has an airfoil structure that defines a first cooling passage and a second cooling passage for directing cooling medium through the airfoil structure, each cooling passage having a swirl structure that imparts tangential velocity on the cooling medium flowing through the associated cooling passage. A method of making an airfoil that includes forming an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure and forming a swirl structure that is operatively associated with the cooling passage and imparts tangential velocity to the cooling medium flowing through the cooling passage.

Abstract: A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.

Abstract: Shot sleeves for high temperature die casting include a nickel-based alloy having a low modulus single crystal with axi-symmetric orientation.

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a core body for at least partially forming an internal passage architecture of a component; and forming an outer skin on the core body in which a core body binder is locally eliminated.

Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.

Abstract: A method for evaluating a turbine component includes inducing a thermal response of the component at an initial time, capturing a two-dimensional infrared image of the thermal response of the component with a thermal imaging device, wherein the two-dimensional infrared image comprises a plurality of infrared image pixels, generating a two-dimension to three-dimension mapping template to correlate two-dimensional infrared image data with three-dimensional locations on the component, mapping at least a subset of the plurality of infrared image pixels of the two-dimensional infrared image to three-dimensional coordinates using the mapping template, and generating a three-dimensional infrared image and infrared data of the component from the mapped infrared image pixels to three-dimensional coordinates, wherein the three-dimensional infrared image and infrared data is used to qualify the component for use.

Abstract: An investment casting system includes a core having at least one fine detail, a shell positioned relative to said core, and a strengthening coating applied at least to the at least one fine detail.

Abstract: A heat exchanger assembly includes an outer manifold defining an outer cavity. An inner cavity is defined by an inner shell supported within the outer manifold and at least partially surrounded by the outer cavity. The inner shell includes a plurality of impingement openings for directing airflow into the inner cavity. An inner manifold is supported within the inner cavity. The inner manifold is exposed to impingement airflow through the plurality of impingement openings in the inner shell. The inner manifold includes a plurality of flow passages and at least one insulator pocket substantially aligned with the plurality of flow passages. A cooled cooling air system for a gas turbine engine and a gas turbine engine assembly are also disclosed.

Abstract: 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.

Abstract: Methods and systems for modulating airflow may include a metering device comprising a face, an aperture through the face being defined by an aperture rim, and a metering appendage disposed adjacent to the aperture and coupled to the aperture rim and/or the face. The metering appendage may comprise a shape memory alloy and may be configured to transition from a first geometry to a second geometry.

Abstract: A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity.

Abstract: This disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal provided between the mate face of the first engine component and the mate face of the second engine component. The seal includes least one trough.

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 tangential on-board injector (TOBI) for a gas turbine engine and methods of making the same are provided. The TOBI includes at least one adjustable strut configured to control an airflow through the TOBI, the at least one adjustable strut moveable to change an airflow characteristic within the TOBI.

Abstract: Systems for tube-to-tube connections are described herein. A device having an aperture for receiving a tube may comprise: an inlet portion comprising a first diameter, the inlet portion located at an inlet of the aperture; a braze filler collector portion located axially adjacent to the inlet portion comprising a second diameter, the second diameter being greater than the first diameter; a necked portion located axially adjacent to the braze filler collector portion comprising a third diameter, the third diameter being less than the first diameter and the second diameter; a flow surface comprising a fourth diameter, the fourth diameter being less than the third diameter, the flow surface defining a void; and a collection pocket located axially adjacent to the necked portion, the collection pocket configured to collect a braze filler material from the necked portion to prevent the braze filler material from contacting the flow surface.

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component includes an additively manufactured skeleton core portion manufactured of a refractory metal, a surround core portion that at least partially encapsulates the additively manufactured skeleton core portion, the surround core portion manufactured of a ceramic material, a surround core portion that at least partially encapsulates the additively manufactured skeleton core portion, the surround core portion manufactured of a ceramic material and a cooling hole shape that extends from the additively manufactured skeleton core portion through the surround core portion, the cooling hole shape operable to form a cooling hole.

Abstract: A gas turbine engine including a compressor section, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a plurality of gas path components exposed to a primary fluid flowpath through the compressor section, the combustor section and the turbine section. At least one of the gas path components includes an exterior facing surface, a lattice structure extending outward from the exterior facing surface, the lattice structure being integral to the exterior facing surface, and a thermal barrier coating adhered to at least a portion of the exterior facing surface and the lattice structure.

Abstract: A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity.

Abstract: A die casting plunger tip assembly includes a first portion having a closed end defining an outer surface, and a tip cover disposed on the outer surface of the closed end.