Abstract: Methods and systems are provided for inferring thickness and volume of one or more object classes of interest in two-dimensional (2D) medical images, using deep neural networks. In an exemplary embodiment, a thickness of an object class of interest may be inferred by acquiring a 2D medical image, extracting features from the 2D medical image, mapping the features to a segmentation mask for an object class of interest using a first convolutional neural network (CNN), mapping the features to a thickness mask for the object class of interest using a second CNN, wherein the thickness mask indicates a thickness of the object class of interest at each pixel of a plurality of pixels of the 2D medical image; and determining a volume of the object class of interest based on the thickness mask and the segmentation mask.

Abstract: A method of metallurgical processing includes, providing a workpiece that has been formed by additive manufacturing of a nickel-chromium based superalloy. The workpiece has an internal porosity and a microstructure with a columnar grain structure and delta phase. The workpiece is then hot isostatically pressed to reduce the internal porosity and to at least partially retain the columnar grain structure and the delta phase. The workpiece is then heat treated to at least partially retain the columnar grain structure and the delta phase.

Abstract: A process for manufacturing a turbine engine component includes the steps of: providing a powder containing gamma titanium aluminide; and forming a turbine engine component from said powder using a direct metal laser sintering technique.

Abstract: A method for forming a part having a dual property microstructure includes the steps of: forming a blank having a narrow top portion and a wide base portion; heating the blank to an elevated temperature; and forming a dual property microstructure in the blank by cooling different portions of the blank at different cooling rates.

Abstract: Components include a low pressure turbine having a plurality of rotor assemblies including a first gamma TiAl intermetallic blade having a maximum operating temperature over 1180° F. (638° C.). At least two of the rotor assemblies include gamma TiAl intermetallic alloy blades. In an embodiment, a method of making a turbine having a plurality of rotor assemblies includes attaching a first gamma TiAl intermetallic alloy blade to an upstream stage of the plurality of rotor assemblies.

Abstract: A process to increase ductility includes utilizing ?-TiAl alloy as a base alloy and reducing at least one interstitial of the base alloy to create an alloy compositions with extremely low interstitials (Eli).

Abstract: An alloy composition including a ?-TiAl alloy with a sustained temperature capability of about 1500 F. An alloy composition including a ?-TiAl alloy with an oxygen level of about 100 wppm and between about 1500-3000 appm carbon. An alloy composition including a ?-TiAl alloy with an alpha stabilizer.

Abstract: A method of metallurgical processing includes, providing a workpiece that has been formed by additive manufacturing of a nickel-chromium based superalloy. The workpiece has an internal porosity and a microstructure with a columnar grain structure and delta phase. The workpiece is then hot isostatically pressed to reduce the internal porosity and to at least partially retain the columnar grain structure and the delta phase. The workpiece is then heat treated to at least partially retain the columnar grain structure and the delta phase.

Abstract: The present disclosure provides a method of preparing superalloy metals having a crystallographic texture controlled micro structure by electron beam melting.

Abstract: Components include a low pressure turbine having a plurality of rotor assemblies including a first gamma TiAl intermetallic blade having a maximum operating temperature over 1180° F. (638° C.). At least two of the rotor assemblies include gamma TiAl intermetallic alloy blades. In an embodiment, a method of making a turbine having a plurality of rotor assemblies includes attaching a first gamma TiAl intermetallic alloy blade to an upstream stage of the plurality of rotor assemblies.

Abstract: A process for manufacturing a turbine engine component includes the steps of: providing a powder containing gamma titanium aluminide; and forming a turbine engine component from said powder using a direct metal laser sintering technique.

Abstract: A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.

Abstract: A process for manufacturing a turbine engine component comprises the steps of: casting ingots made of a gamma TiAl material using a double vacuum arc remelting casting technique; subjecting the cast ingots to a hot isostatic pressing to close porosity; forming at least one pancake of the gamma TiAl material by isothermally forging the hot isostatic pressed ingots; sectioning each pancake into a plurality of blanks; heat treating the blanks to produce a desired microstructure and mechanical properties; and machining the blanks into finished turbine engine components. A system for performing the process is also disclosed.

Abstract: A method for forming a part having a dual property microstructure includes the steps of: forming a blank having a narrow top portion and a wide base portion; heating the blank to an elevated temperature; and forming a dual property microstructure in the blank by cooling different portions of the blank at different cooling rates.

Abstract: A process for manufacturing a turbine engine component comprises the steps of: casting ingots made of a gamma TiAl material using a double vacuum arc remelting casting technique; subjecting the cast ingots to a hot isostatic pressing to close porosity; forming at least one pancake of the gamma TiAl material by isothermally forging the hot isostatic pressed ingots; sectioning each pancake into a plurality of blanks; heat treating the blanks to produce a desired microstructure and mechanical properties; and machining the blanks into finished turbine engine components. A system for performing the process is also disclosed.

Abstract: A process for producing sheets of ?-TiAl includes the steps of forming a melt of a ?-TiAl alloy; casting the ?-TiAl alloy to form an as-cast ?-TiAl alloy; encapsulating the as-cast ?-TiAl alloy to form an as-cast ?-TiAl alloy preform; and rolling the as-cast ?-TiAl alloy preform to form a sheet comprising ?-TiAl.

Abstract: A method of processing a workpiece of maraging steel includes receiving a workpiece of maraging steel that has been subjected to thermomechanical processing at an austenite solutionizing temperature and then directly aging the workpiece of maraging steel at an aging temperature to form precipitates within a microstructure of the workpiece of maraging steel, without any intervening heat treatments between the thermomechanical processing and the direct aging.

Abstract: Systems and methods for transient liquid phase bonding are described herein. Embodiments of these systems and methods utilize sandwich interlayers to produce stronger, more homogeneous bonds than currently possible. These sandwich interlayers have a middle bonding layer sandwiched between two outer bonding layers. The middle bonding layer is a different composition, and may even be a different form, than the outer bonding layers. In embodiments, these sandwich interlayers may be used to join a single crystal material to a polycrystalline material to make a gas turbine engine component, such as an integrally bladed rotor.

Abstract: A process for producing sheets of ?-TiAl includes the steps of forming a melt of a ?-TiAl alloy; casting the ?-TiAl alloy to form an as-cast ?-TiAl alloy; encapsulating the as-cast ?-TiAl alloy to form an as-cast ?-TiAl alloy preform; and rolling the as-cast ?-TiAl alloy preform to form a sheet comprising ?-TiAl.

Abstract: Components produced by powder metallurgy techniques are described herein. Embodiments of these components have little or no porosity therein after processing. Embodiments of these components are created by creating a preform from a powder; creating a component from the preform; heat treating the component to create a predetermined microstructure therein; and then hot isostatic pressing the heat treated component to reduce any porosity therein. The components can then be machined to their final dimensions, if necessary.