General Electric Company

Paul Mathew

Ravindra Shankar Ganiger

David Raju Yamarthi

Mohandas Nayak

Surinder Singh Pabla

Krishnamurthy Anand

Gautam Suresh Naik

Hiranya Kumar Nath

Yuk-Chiu Lau

Ramasamy Thiyagarajan

Vidyashankar Ramasastry Buravalla

Sriram Krishnamurthy

Guruprasad Sundararajan

Nikhil Subhashchandra Tambe

Sathisha Chikkabikkodu Hanum

Pankaj Dhaka

Norman Arnold Turnquist

Ronald Ralph Cairo

David Vincent Bucci

Kudum Shinde

Monty Lee Shelton

Gary Willard Bryant, Jr

Sharad Pundlik Patil

Eklavya Calla

Michael Joseph Murray

Sundar Amancherla

Vishnu Vardhan Venkata Tatiparthi

Mandyam Rangayan Sridhar

Parmeet Singh Chhabra

Biju Dasan

Deoras Prabhudharwadkar

Douglas Lorrimer Armstrong

Maruthi Manohar Jupudi

Bouria Mohamed Faqihi

Rachamadugu Sivaprasad

Souvik Porel

Vasanth Kumar Balaramudu

Narayanan Janakiraman

Nuthi Srinivas

Krishnendu Saha

Duraiswamy Srinivasan

Shanmuga Priyan Subramanian

Sreerama Prasad Ramaswamy

Murali Krishna Kalaga

Jose Antonio Cuevas Alvarez

Harsha K A

Ritwik Biswas

A coated component includes a component having a surface, and a solid lubricant wear resistant coating on the surface, wherein the solid lubricant wear resistant coating includes a solid lubricant phase with a negative thermal expansion coefficient material dispersed therein. The component may also include a coating having oleophilic or porous properties disposed on portions thereof, and a coating having oleophobic properties disposed on portions thereof.

Coatings and coated component

A bearing having a bearing surface with a groove, the bearing positioned adjacent to a shaft, the groove facing the shaft, and a negative thermal expansion (NTE) material positioned in the groove, the NTE material at least partially filling the groove.

Bearings with grooves and methods of producing the same

An anti-fretting coating composition that is operationally stable at temperatures of 800° F. to 2650° F. is provided. The anti-fretting coating composition primarily includes cobalt and aluminum oxide and may also include other modifying phases that enhance the overall tribological performance. A component coated with the anti-fretting coating composition is also provided. The component includes a substrate having a first contact surface shaped to cooperate with a second contact surface of an abutting member in a manner which can develop wear between the first contact surface and the second contact surface. The first contact surface includes an anti-fretting coating thereon formed from the disclosed anti-fretting coating composition.

Anti-fretting coating composition and coated components

Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes a first annular substrate extending along an axial direction, the first annular substrate defining a cavity at a radially inward surface of the first annular substrate, a second annular substrate positioned at least partially within the cavity of the first annular substrate, and a tension belt extending circumferentially around a periphery of the second annular substrate.

Variable flowpath casings for blade tip clearance control

A gearbox assembly for a gas turbine engine includes a hollow gear. The hollow gear has one or more reservoirs configured to store a lubricant and one or more passages configured to supply the lubricant to one or more gear meshes in the gearbox assembly. The hollow gear provides a dampening system configured to absorb vibrations and loading experienced in the gearbox assembly and configured to provide impact resistance for the gearbox assembly.

Gearbox assembly

Methods and apparatus to maintain a state of a fluid in a system are disclosed. An example system includes a pump including a primary inlet, a primary outlet, and a secondary inlet, at least one injector including a first inlet, a second inlet, and at least one outlet, a third conduit coupled to a first conduit upstream of the primary inlet and coupled to the at least one injector at the first inlet to deliver the fluid, a fourth conduit coupled to a second conduit downstream of the primary outlet and coupled to the at least one injector at the second inlet to deliver the fluid, and a fifth conduit coupled to the at least one injector at the at least one outlet to receive the fluid and coupled to the pump at the secondary inlet.

Methods and apparatus to maintain a state of a fluid in a system

A method for cooling a compressor section of a gas turbine engine includes sensing, via at least one first temperature sensor, a first temperature at the first location on a stationary assembly of the compressor section. The method also includes sensing, via at least one second temperature sensor, a second temperature at a second location on the stationary assembly of the compressor section. The second location is spaced apart from the first location. The method also includes determining, via a controller, a delta between the first temperature and the second temperature. Further, the method includes operating, via the controller, at least one cooling element when the delta exceeds a predetermined threshold, the at least one cooling element provided at the first location of the stationary assembly of the compressor section.

System and method for providing cooling in a compressor section of a gas turbine engine

An airfoil assembly and a method of manufacturing the same are provided, the airfoil assembly defining a span axis, a root end, and a tip end. The airfoil assembly includes a reinforcement structure comprising a first helical support structure wrapped around the span axis between the root end and the tip end and a second helical support structure wrapped around the span axis between the root end and the tip end; a polymeric matrix material positioned at least partially around the reinforcement structure; and an outer skin positioned around the reinforcement structure and the polymeric matrix material.

Airfoil assembly with an internal reinforcement structure

Mitigating particulate intrusion to an air intake system of a gas turbine system with intrusion protective coatings tailored to locale of operation. A particulate intrusion protective coating is applied to a surface of a component of the air intake system to mitigate ingress of particulates within the air intake system and the gas turbine system. The particulate intrusion protective coating includes one or more particulate ingress influencing properties tailored to the common attributes of the particulates associated with the locale of operation of the gas turbine engine and the air intake system. The particulate ingress influencing properties affect rebounding and coalescing characteristics of the particulates at a point of impact with the applied surface having the particulate intrusion protective coating, entraining the particulates at the point of impact and inhibiting further ingress along an inlet air flow path of the air intake system into the gas turbine engine.

System and method for mitigating particulate intrusion to an air intake system of a gas turbine system with intrusion protective coatings tailored to locale of operation

A component susceptible to the formation of deposits, such as a component of a hydrocarbon system in a gas turbine engine. The component includes a substrate having a surface susceptible to the formation of a deposit thereon. A shape memory alloy coating is formed on the surface of the substrate. The shape memory alloy coating is a plurality of particles formed on the surface, and each particle of the plurality of particles is formed from a shape memory alloy.

Surface with shape memory alloy particles

A method for manufacturing a blade structure includes providing the blade structure comprising an outer surface having an aerodynamic profile. The method also includes applying one or more shape memory alloys to the outer surface of the blade structure so as to form an outer protection layer on at least a portion of the blade structure. Moreover, the method includes securing the one or more shape memory alloys to the blade structure.

Methods for manufacturing blade structures

A rotor blade assembly for a wind turbine includes at least one rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a blade tip and a blade root. The surfaces are constructed of a polymeric composite material. The rotor blade assembly also includes a protection cap arranged adjacent to one or more of the surfaces of the rotor blade so as to cover at least a portion of the one or more surfaces of the rotor blade. The protection cap includes a body defining an overall length. Further, at least a first segment of the protection cap is constructed of a tungsten-based metal. Thus, the protection cap is configured to reduce erosion and resist corrosion of the rotor blade caused by particle or liquid impact.

Tungsten-based erosion-resistant leading edge protection cap for rotor blades

A filled abradable seal component, an associated method of manufacturing, and a turbomachine including the filled abradable seal component are disclosed. The method includes positioning the abradable seal component including a plurality of honeycomb cells, applying a filler material on the abradable seal component to fill the plurality of honeycomb cells, and curing the filler material at a temperature below 250 degrees Celsius to produce the filled abradable seal component. The filler material includes an abradable material, a binder material, and a fluid catalyst. The abradable material includes at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material includes at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate. The fluid catalyst includes a solvent having hydroxyl groups.

Filled abradable seal component and associated methods thereof

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

An appliance for washing objects is disclosed that effectively and energy-efficiently filters oil-based residue from a fluid such as washing fluid that drains from a basin in the appliance. In one illustrative embodiment, an appliance includes a novel filter assembly for filtering oil-based residue out of the washing fluid. The filter assembly includes a filter layer composed of a material that is both oleophilic and hydrophobic. The filter assembly forms part of a fluid distribution system that has different configurations. A first configuration allows for recirculating filtered wash fluid from an outlet of the filter assembly back into the basin of the appliance. A second configuration allows for draining both the washing fluid from the outlet of the filter assembly and the oil-based residue from a bypass zone of the filter assembly to an appliance outlet.

Device and implementation for filtering oil from water in an appliance

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Bengaluru, India

Paul Mathew