General Electric Company

General Electric Technology Gmbh

Global Life Sciences Solutions USA LLC

Deoras Prabhudharwadkar

Jalal Hunain Zia

Ashok Gopinath

Majed Sammak

Maruthi Manohar Jupudi

Krishnendu Saha

Bradly Aaron Kippel

Mohandas Nayak

Christopher Joseph Homison

Paul Mathew

Bouria Mohamed Faqihi

Fadi Ghaith

Ashok Kumar Balumuri

Jalal Zia

Disclosed is an exhaust duct () for a gas turbine engine (), comprising a silencer section (). At least two plate-shaped silencer baffles () are provided inside the silencer section (). At least one of the plate-shaped silencer baffles is configured as a heat exchange device in that it comprises at least one internal cavity () suitable for receiving a heat exchange fluid and leakproof with respect to the interior of the exhaust duct, wherein the at least one internal cavity is fluidly connected to the outside of the exhaust duct at an inlet port and an outlet port (). This device is useful for recuperating exhaust heat from exhaust gases of the gas turbine engine without the expense and additional space required for providing a heat recovery steam generator.

Exhaust duct for a gas turbine engine

An impeller, for example, a Rushton impeller for a bioreactor system is disclosed. The impeller includes a hub, optionally including a slot, a plurality of blades, and one or more turbulators. The plurality of blades is disposed along a circumferential direction of the hub and spaced apart from each other. Each of the plurality of blades is coupled to at least a portion of a circumference and/or a top surface of the hub. Each blade of the plurality of blades includes a pressure face and a suction face. The one or more turbulators is disposed on at least a portion of the suction face, the pressure face, or both, of a blade of the plurality of blades.

Impeller including one or more turbulators, for a bioreactor system

A power generation system includes a combustion system, a turbocharger, and a heat recovery system. The combustion system is configured to combust a fuel with a flow of air. The combustion system is further configured to generate an exhaust stream. The turbocharger is configured to compress a flow of compressed air and to channel the flow of compressed air to the combustion system. The combustion system is configured to combust the fuel with the flow of compressed air and an additional flow of air. The heat recovery system is configured to recover heat from the exhaust stream and to drive the turbocharger. The heat recovery system uses a supercritical working fluid to absorb heat from the exhaust stream and to drive the turbocharger.

Systems and methods for operating a turbocharged gas turbine engine

An evaporative cooling system for a gas turbine includes a first plurality of evaporative cooling media, spaced from the other evaporative cooling media. The system also includes a plurality of valves, with water flowing through at least one valve to fully wet at least one evaporative cooling medium. In one mode of operation, at least one evaporative cooling medium remains dry.

Variable evaporative cooling system

A turbocharger system includes a low pressure turbocharger (LPT) that includes an LPT compressor and an LPT turbine. The turbocharger system is configured to divide ambient air compressed by the LPT compressor into a heat exchanger flow and an HPT compressor inlet flow. The turbocharger system also includes a high pressure turbocharger (HPT) that includes an HPT compressor and an HPT turbine. The HPT compressor is configured to further compress the HPT compressor inlet flow, which is then channeled to a rotary machine as auxiliary compressed air. The turbocharger system further includes a heat exchanger configured to place the heat exchanger flow into thermal communication with exhaust gases associated with the rotary machine. The discharged heat exchanger flow is divided into parallel streams, and the LPT turbine and the HPT turbine are each configured to be driven by a respective one of the parallel streams.

Turbocharger system for a rotary machine and method of assembling the same

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

Labyrinth seal system includes stationary component and rotatable component, where one of the stationary and rotatable components includes teeth. The labyrinth seal system further includes abradable component coupled to surface of other of the stationary and rotatable components and disposed facing the teeth. The abradable component includes a plurality of honeycomb cells disposed adjacent to each other along axial direction and circumferential direction. Each honeycomb cell includes a plurality of radial sidewalls, where each radial sidewall includes first portion and second portion. The first portion is coupled to the surface and the second portion extends from the first portion towards clearance defined between the stationary and rotatable components. The second portion is bent relative to radial axis of the labyrinth seal system.

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Dubai, United Arab Emirates

Deoras Prabhudharwadkar