General Electric Company

Ge Infrastructure Technology, LLC

Ge Renewable Technologies

Krishnamurthy Anand

Surinder Singh Pabla

Sundar Amancherla

Eklavya Calla

Jon Conrad Schaeffer

David Vincent Bucci

Dennis Michael Gray

Warren Arthur Nelson

Paul Mathew

Biju Dasan

Gerald Burt Kliman

Paul Stephen DiMascio

Pazhayannur Ramanathan Subramanian

Yuk-Chiu Lau

Mohandas Nayak

Joshua Lee Margolies

Luana Emiliana Iorio

Guruprasad Sundararajan

Pierre Montagne

David Terry Trayhan, Jr

Lacey Lynn Schwab

Padmaja Parakala

Vinod Kumar Pareek

Maher Mohamad Aboujaib

Sathisha Chikkabikkodu Hanum

Matthieu Paul Frederic Vierling

Srinidhi Sampath

Amitabh Verma

Olav Rommetveit

Suchismita Sanyal

Abdurrahman Abdallah Khalidi

Ravikiran Kopparthi

Hans Aunemo

Alain Demers

Eklayva Calla

James Anthony Ruud

Wayne Charles Hasz

Don Mark Lipkin

Canan Uslu Hardwicke

Carey Shawn Rogers

Ronald Ralph Cairo

Farshad Ghasripoor

Paul A Siemers

Michael Francis Xavier Gigliotti

Rebecca Evelyn Hefner

Atanu Saha

Liang Jiang

Iacopo Giovannetti

Massimo Giannozzi

Steven Alfred Tysoe

Karthick Vilapakkam Gourishankar

Bhaskar Tamma

Hari Nadathur Seshadri

Richard Arthur Nardi, Jr

Subhrajit Dey

Seung-Woo Choi

Nuo Sheng

Luc Stephane Leblanc

Joydeep Pal

Filippo Cappuccini

Thodla Ramgopal

Jonathan Paul Blank

Sanjay Kumar Sondhi

Jane Marie Lipkin

Savio Sebastian Kathayanatt

Bala Srinivasan Parthasarathy

John William Short

Ramkumar Kashyap Oruganti

Paul Matthew Thomas

Tamara Jean Muth

Rajesh Panchal

Priyanka Saxena

Nicole Barbara Piche

Nitin Jayaprakash

Kanchan Kumari

Guru Prasad Sundararajan

Prajina Bhattacharya

Ritwik Biswas

Paul Stephen Dimascio

Prazhayannur Ramanathan Subramanian

Ramkumar Oruganti

Santosh Angadi Shruti

A method includes applying a material coating on a surface of a machine component using a thermal spray, wherein the material coating is formed from a combination of a hardfacing material and aluminum-containing particles. The method also includes thermally treating the material coating to generate an oxide layer comprising aluminum from the aluminum-containing particles, wherein the oxide layer is configured to reduce oxidation of the hardfacing material.

Oxidation and wear resistant coating

Various embodiments include a dense abradable coating, a method of reducing rub damage to a turbine engine part by applying the dense abradable coating thereto, and a turbine engine part having the abradable coating thereon. Particular embodiments include a dense abradable coating including a pore-free metallic composite, a high-aluminum containing brittle alloy, and a plurality of hollow abradable particles.

Dense abradable coating with brittle and abradable components

A system includes a turbine combustor and one or more supply circuits configured to supply one or more fluids to the turbine combustor. The one or more supply circuits include at least a liquid fuel supply circuit fluidly coupled to a liquid fuel source and configured to supply a liquid fuel from the liquid fuel source to the turbine combustor. The system also includes a corrosion inhibitor injection system including a magnesium source storing a magnesium-based inhibitor that includes magnesium oxide (MgO) and an yttrium source storing an yttrium-based inhibitor that includes yttrium oxide (YO). The corrosion inhibitor injection system is fluidly coupled to the turbine combustor and the one or more supply circuits, and is configured to inject the magnesium-based inhibitor and the yttrium-based inhibitor as vanadium corrosion inhibitors into the turbine combustor or the one or more supply circuits.

Systems and methods for vanadium corrosion inhibitors

A system for coating a component is provided. The system includes a feedstock supply, a carrier fluid supply, and a thermal spray gun coupled in flow communication with the feedstock supply and the carrier fluid supply. The feedstock supply contains a substantially homogeneous powder mixture of a first powder and a second powder. The second powder is softer than the first powder and has a percentage by mass of the powder mixture of between about 0.1% and about 3.0%.

Feedstocks for use in coating components

A corrosion monitoring system includes at least one corrosion sensor. The corrosion sensor includes a metallic plug having at least one opening, at least one ceramic sheath in the opening of the metallic plug, and a plurality of probes. Each probe has a central portion with a predetermined cross sectional area extending from the metallic plug. The ceramic sheath electrically isolates each first end and each second end of the probes from the metallic plug and the other first ends and second ends. The probes are sized to provide a distribution of predetermined cross sectional areas of the central portions. The corrosion monitoring system also includes a resistance meter measuring an ohmic resistance for at least one of the probes and a computer determining a corrosion rate by correlating a rate of change of the ohmic resistance to the corrosion rate of the probe.

Corrosion sensor, corrosion monitoring system, and method of quantifying corrosion

A process based on the combined use of yttrium and magnesium to inhibit vanadium corrosion of high temperature parts of thermal equipment. The combined use of yttrium and magnesium, applied in a variable yttrium/magnesium ratio, compared with conventional magnesium inhibition, may reduce emission of magnesium vanadate and minimize losses of performance due to fouling of the high temperature parts, including in the presence of alkali metals. Further, compared with inhibition based on yttrium alone, it may reduce the inhibition cost and reinforce the protection against combined vanadium pentoxide and sodium sulfate corrosion.

Yttrium and magnesium based vanadium corrosion inhibitors

A composition for a reinforced metal matrix coating, and a method of preparing and coating the composition. The composition includes a plurality of sacrificial metallic binder particles that is anodic with respect to a base substrate, and a plurality of hard particles.

Turbine blade coating composition

A process of forming a calcium-magnesium-aluminosilicate (CMAS) penetration resistant coating, and a CMAS penetration resistant coating are disclosed. The process includes providing a thermal barrier coating having a dopant, and exposing the thermal barrier coating to calcium-magnesium-aluminosilicate and gas turbine operating conditions. The exposing forming a calcium-magnesium-aluminosilicate penetration resistant layer. The coating includes a thermal barrier coating composition comprising a dopant selected from the group consisting of rare earth elements, non-rare earth element solutes, and combinations thereof. Additional or alternatively, the coating includes a thermal barrier coating and an impermeable barrier layer or a washable sacrificial layer positioned on an outer surface of the thermal barrier coating.

Calcium-magnesium-aluminosilicate resistant coating and process of forming a calcium-magnesium-aluminosilicate resistant coating

A coating, a coating system, and a coating method are provided. The coating includes between about 0.25-35% filler particles embedded in a chrome phosphate binder matrix comprising a balance of the coating by volume. The filler particles have a size in the range from nanosize to six microns with an aspect ratio of from 1:1 to 3:1, and include up to 100% by weight lubricious particles with a balance hard particles. The lubricious particles are selected from the group consisting of boron nitride (BN), titanium nitride (TiN), titanium oxide (TiO), zinc (Zn), tin (Sn), oxides of zinc and tin, and combinations thereof. The hard particles are selected from the group consisting of chromium carbide (CrC), tungsten carbide (WC), silicon (Si), aluminum (Al), oxides or nitrides of silicon and aluminum, and combinations thereof. A green slurry coating includes an evaporable solvent mixed with the filler particles and chrome phosphate binder matrix.

Coating, coating system, and coating method

A method for fabricating thermal barrier coatings. The thermal barrier coatings are produced with a fine grain size by reverse co-precipitation of fine powders. The powders are then sprayed by a solution plasma spray that partially melts the fine powders while producing a fine grain size with dense vertical cracking. The coatings comprise at least one of 45%-65% YbOthe balance zirconia (zirconium oxide), Yb/Y/Hf/Ta the balance zirconia (zirconium oxide) and 2.3-7.8% La, 1.4-5.1% Y and the balance zirconia (zirconium oxide) and are characterized by a thermal conductivity that is about 25-50% lower than that of thermal barrier coatings comprising YSZ. The thermal barrier coatings also are characterized by at least one of excellent erosion resistance, fracture toughness and abrasion resistance.

Architectures for high temperature TBCs with ultra low thermal conductivity and abradability and method of making

A titanium aluminide application process and article with a titanium aluminide surface are disclosed. The process includes cold spraying titanium aluminide onto an article within a treatment region to form a titanium aluminide surface. The titanium aluminide surface includes a refined gamma/alpha2 structure and/or the titanium aluminide is cold sprayed from a solid feedstock of a pre-alloyed powder.

Titanium aluminide application process and article with titanium aluminide surface

A seal system, for an apparatus that includes a rotatable portion with airfoils coupled thereto and a stationary portion with an inner surface, includes an abradable portion including at least one abradable layer of an abradable material formed over the inner surface. The seal system also includes an abrading portion disposed over at least a portion of a substrate of the airfoil. The abrading portion includes at least one abrading layer formed on at least a portion of the substrate and a plurality of abrasive particles embedded within the abrading layer. The plurality of abrasive particles includes at least one of substantially all of one of tantalum carbide (TaC), aluminum oxide (AlO), and ziconia (ZrO), cubic boron nitride (cBN) and AlOin predetermined ratios, cBN, AlOand ZrOin predetermined ratios, AlOand ZrOfused together in predetermined ratios, and TaC and AlOin predetermined ratios.

Seal systems for use in turbomachines and methods of fabricating the same

A compressor blade for use in a compressor section of a gas turbine engine, comprising: a martensitic stainless steel compressor blade and an abrasive coating having an anodic component. The compressor blade has a blade portion, a dovetail portion and a platform portion intermediate the blade portion and the dovetail portion, the blade portion terminating in a tip opposite the dovetail portion. A cobalt-based coating overlies at least the blade portion of the compressor blade. The cobalt-based coating comprises a cobalt based material that includes precipitates of tungsten carbide that provide erosion resistance and particles of a sacrificial metal-based material distributed through the cobalt-based coating that provide galvanic corrosion resistance to the system.

Erosion and corrosion resistant coatings for exhaust gas recirculation based gas turbines

A self-lubricating brush seal assembly, for a power generation system and method of reducing air leakage in a power generation system including a plurality of self-lubricating members is provided. The plurality of self-lubricating members include a plurality of self-lubricating bristles, a plurality of cores sheathed in a self-lubricating braid, a plurality of cores having an outer diameter coated with self-lubricating material and a solid lubricating pack. The lubricating material is selected from graphite, hexagonal-boron nitrite (hBN), molybdenum disulfide (MoS), tungsten disulfide (WS), titanium nitride (TiN), titanium aluminum nitride (TiAlN), titanium carbonitride (TiCN), and combinations thereof.

Self-lubricating brush seal assembly and method of reducing leakage

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Bengaluru, India

Krishnamurthy Anand