General Electric Company

Other

Frederic Joseph Klug

Wayne D Pasco

Irvin C Huseby

Shyh-Chin Huang

Svante Prochazka

Bernard Patrick Bewlay

Marcus P Borom

Robert Arthur Giddings

Paul Steven Svec

Ronald Scott Bunker

Michael Francis Xavier Gigliotti

Stephen Francis Bancheri

Asish Ghosh

John Eric Tkaczyk

Charles D Greskovich

Chris A Sumpter

Philip Harold Monaghan

Jayantha Amarasekera

Larry Neil Lewis

Venkat Subramaniam Venkataramani

Michael Joseph O'Brien

Ronald H Arendt

Robert John Zabala

Xi Yang

David Martin Johnson

Stephen Francis Rutkowski

Dan Hancu

Daniel George Norton

Robert Joseph Lyons

Tao Li

Hrishikesh Keshavan

Anthony Yu-Chung Ku

Lawrence Donald Graham

Nirm Velumylum Nirmalan

Toby George Darkins, Jr

Thomas Francis McNulty

Elliott West Shanklin

Benjamin Hale Winkler

John Thomas Leman

Matthew Joseph Alinger

Anteneh Kebbede

Roger John Petterson

Kenneth W Lay

Susan Marie Hyde

Cathleen Ann Hoel

Sylvia M DeCarr

Robert Mark Garlock

Subramaniam Venkataramani

Daniel Joseph Lewis

Gabriel Kwadwo Ofori-Okai

John Patrick Pollinger

Sylvia Marie Decarr

Andrea Jeanne Howard

Zachary Kenneth Mowry

Ayesha Maria Gonsalves

Matthew Thomas Johnson

Thomas Francis Mcnulty

Methods for forming ceramic cores are disclosed. A ceramic core formed using the method of the present application includes a silica depletion zone encapsulating an inner zone. The inner zone includes mullite and the silica depletion zone includes alumina. The method includes heat-treating a ceramic body in a non-oxidizing atmospheric condition for an effective temperature and time combination at a pressure less than 10atmosphere to form the silica depletion zone at a surface of the ceramic core.

Methods for forming ceramic cores

A turbine airfoil component assembly for use with a turbine engine including a attachment assembly having an inner surface defining a cavity. The attachment assembly includes a metal alloy substrate. An airfoil assembly is at least partially positioned within the attachment assembly and extends outwardly from the attachment assembly. The airfoil assembly includes a ceramic matrix composite (CMC) substrate. A reaction barrier coating is disposed over at least a portion of the airfoil assembly. The reaction barrier coating is positioned between the attachment assembly and the airfoil assembly.

Turbine airfoil component assembly for use in a gas turbine engine and methods for fabricating same

The present invention details a process for producing a catalyst powder. The steps of the process include preparing catalyst slurry, drying, pyrolyzing, and calcining the catalyst slurry to obtain a calcined catalyst powder. The catalyst slurry comprises a catalyst, a liquid carrier, a templating agent, and a catalyst substrate. The catalyst slurry is dried to obtain a raw catalyst powder. The raw catalyst powder is heated in a first controlled atmosphere to obtain a pyrolyzed catalyst powder and the pyrolyzed catalyst powder is calcined in a second controlled atmosphere to obtain a calcined catalyst powder. A method of fabricating a catalyst surface and catalytic converter using the prepared catalyst powder is also illustrated.

Process for preparing catalyst powder

A method of preparing a solid oxide fuel cell is described herein, as well as the fuel cell itself. The method comprises forming a cathode layer comprising a strontium composition on a ceramic electrolyte layer; and forming a barrier layer between the cathode layer and an overlying interconnect structure comprising chromium, so as to substantially prevent the formation of strontium chromate.

Barrier coatings for interconnects; related devices, and methods of forming

A rare earth-based core for use in the casting of a reactive metal is described. The core contains a ceramic composition which includes at least about 10% by weight of monoclinic rare earth aluminate (REAlO), wherein RE represents at least one rare earth element; and at least about 10% by weight of at least one free rare earth oxide. The ceramic phase of the composition may include a microstructure which comprises a multitude of substantially spherical pores which are formed as a result of the removal of aluminum metal from the core composition during a heat treatment step. Additional embodiments relate to a method for the fabrication of a ceramic core, employing a rare earth oxide, aluminum metal, and a binder. Methods for removing cores from a cast part are also described.

Ceramic cores for casting superalloys and refractory metal composites, and related processes

Compositions suitable for use as cores and shell molds for casting of reactive metal alloys, and casting processes for producing components from such alloys. The composition contains a sintered particulate material of hafnia and at least one additional metal oxide in amounts to yield a ceramic composition containing up to 70 molar percent of hafnia, wherein the additional metal oxide is a rare-earth oxide, the sintered particulate material contains first and second phases, the first phase is the rare-earth oxide and hafnia in solid solution, the second phase is a compound of the rare-earth oxide and hafnia, and the second phase is less reactive with the reactive metal alloy than the first phase.

Hafnia-modified rare-earth metal-based ceramic bodies and casting processes performed therewith

A method of fabricating a core for a ceramic shell mold is disclosed. A porous core body is formed from at least about 50% by weight of at least one rare earth metal oxide. The core body is heated under heating conditions sufficient to provide the core with a density of about 35% to about 80% of its theoretical density. The core body is then infiltrated with a liquid colloid or solution of at least one metal oxide compound, e.g., rare earth metal oxides; silica, aluminum oxide, transition metal oxides, and combinations thereof. The infiltrated core body is then heated to sinter the particles without substantially changing the dimensions of the core body. Mold-core assemblies which include such a core body are also described. A description of processes for casting a turbine component, using the core, is also set forth herein.

Rare earth-based core constructions for casting refractory metal composites, and related processes

A blade cover cooling apparatus comprises a blade cover top plate, comprising a plurality of upper ribs, a blade cover bottom plate, comprising a plurality of lower ribs. The blade cover top plate is disposed over the blade cover bottom plate. The upper ribs are disposed at a first angle and the lower ribs are disposed at a second angle with respect to the blade circumferential reference line, respectively to form a plurality of flow redirection areas. The blade cover bottom plate is disposed to pass a coolant from the turbine blade to the blade cover top plate. A fabrication method aligns the blade cover top plate and the blade cover bottom plate to form the plurality of flow redirection areas.

Turbine blade cover cooling apparatus and method of fabrication

An airfoil for an internal combustion engine, such as a gas turbine, formed by use of a preform. The airfoil includes: an outer surface forming the foil shape; and a plurality of craze-free cooling passages extending through the airfoil. In the preferred embodiment, a root on the airfoil joins the airfoil to the hub of a gas turbine vane assembly. Also, in the preferred embodiment, the gas turbine vane assembly is adapted to receive replaceable airfoils.

Gas turbine having alloy castings with craze-free cooling passages

A method of removing substantially all of the volatile component in a green, volatile-containing ceramic article is disclosed. The method comprises freezing the ceramic article; and then subjecting the frozen article to a vacuum for a sufficient time to freeze-dry the article. Frequently, the article is heated while being freeze-dried. Use of this method efficiently reduces the propensity for any warpage of the article. The article is often formed from a ceramic slurry in a gel-casting process. A method for fabricating a ceramic core used in investment casting is also described.

Method for removing volatile components from a gel-cast ceramic article

The present invention provides a cooling apparatus for cooling a turbine blade. The cooling apparatus comprises a pressure side plate comprising a plurality of pressure ribs, a suction side plate comprising a plurality of suction ribs, and a plurality of flow redirection areas. The pressure side plate is disposed over the suction side plate, where the pressure ribs are disposed at a first angle with respect to a blade span reference line and the suction ribs are disposed at a second angle with respect to the blade span reference line, to form the flow redirection areas. The present invention provides a method of fabricating the cooling apparatus for the turbine blade comprising aligning the pressure side plate and the suction side plate to form the plurality of flow redirection areas between the pressure side plate and the suction side plate.

Turbine blade core cooling apparatus and method of fabrication

A turbine blade comprises an external pressure side plate comprising a plurality of external pressure ribs, an internal pressure side plate comprising a plurality of internal pressure ribs, and a plurality of pressure flow redirection areas. The external pressure side plate is disposed over the internal pressure side plate to form a pressure side double wall. The external pressure ribs are disposed at a first angle with respect to a blade span reference line and the internal pressure ribs are disposed at a second angle with respect to the blade span reference line to form the pressure flow redirection areas. The pressure side double wall is configured to pass a coolant through the pressure side double wall. A fabrication method aligns the external pressure side plate and the internal pressure side plate to form the pressure flow redirection areas between the external pressure side plate and the internal pressure side plate.

Turbine blade wall cooling apparatus and method of fabrication

A ceramic casting shell mold having a pre-selected shape comprises alternate, repeating layers of a ceramic coating material and a ceramic stucco, defining a total thickness of the shell mold; and a ceramic-based reinforcing sheet disposed in the alternate, repeating layers of coating material and stucco at an intermediate thickness. The ceramic-based reinforcing sheet comprises a one-piece monolithic, integral body, which comprises a pattern of holes that enhance bonding between the ceramic-based reinforcing sheet and adjacent ones of the alternate, repeating layers of ceramic coating material. The ceramic-based reinforcing sheet conforms to the shape of the mold and providing structural reinforcement to the mold.

Reinforced ceramic shell molds, and related processes

A method for shielding a molten metal cooling bath used in directional casting of superalloys from a high temperature furnace environment. A plurality of floating ceramic baffles are used, floated on the top of such cooling bath so as to substantially cover the surface thereof. Each baffle member comprises a hollow ceramic member and ceramic seal means sintered to such hollow member so as to form a hermetically sealed chamber within the hollow member. The baffles are displaced during the directional casting process when a mold containing the cast article is lowered into the cooling bath. A ceramic baffle of this construction is also disclosed.

Floating insulating baffle for high gradient casting

Growing community of inventors

Schenectady, NY, United States of America

Frederic Joseph Klug