United Technologies Corporation

Raytheon Technologies Corporation

Gopal Das

Gabriel L Suciu

James D Hill

Brian D Merry

Dilip M Shah

Ioannis Alvanos

Thomas DeMichael

Allan R Penda

Michael A Moulin

Luliana Cernatescu

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.

Metallurgical process with nickel-chromium superalloy

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.

Process for manufacturing a gamma titanium aluminide turbine component

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.

Gamma titanium dual property heat treat system and method

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&#xb0; F. (638&#xb0; 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.

Advanced gamma TiAl components

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.

Process and system for fabricating gamma TiAl turbine engine components

A process for producing sheets of &#x3b3;-TiAl includes the steps of forming a melt of a &#x3b3;-TiAl alloy; casting the &#x3b3;-TiAl alloy to form an as-cast &#x3b3;-TiAl alloy; encapsulating the as-cast &#x3b3;-TiAl alloy to form an as-cast &#x3b3;-TiAl alloy preform; and rolling the as-cast &#x3b3;-TiAl alloy preform to form a sheet comprising &#x3b3;-TiAl.

Direct rolling of cast gamma titanium aluminide alloys

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.

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Simsbury, CT, United States of America

Gopal Das