General Electric Company

Ge Infrastructure Technology, LLC

Exxonmobil Upstream Research Company

Rajarshi Saha

Gilbert Otto Kraemer

Indrajit Mazumder

Bhaskar Pemmi

Anil Kumar Sharma

Santhosh Donkada

Prashant Kumar

Sabarinath Devarajan

Anil Kumar Dasoji

Jeevankumar Krishnan

Richard Alan Huntington

Laxmikant Merchant

Franklin F Mittricker

Robert Frank Hoskin

Harish Bommanakatte

Sheo Narain Giri

Seyfettin Can Gulen

Sanjeev Kumar Jha

Qiong Zhou

Venugopala Durwasula Raju

Chandrasekhar Pushkaran

Sudhakar Todeti

Mohamad-Maher Aboujaib

Bouria Mohamed Faqihi

Prabhakaran Saraswathi Rajesh

Durgaprasad Janapaneedi

Paul Roberts Scarboro

Pramod Kumar Biyani

Sindhu Penna

Vivekanandhan Thiruvettipuram Madhivanan

Krishna Kishore Gumpina

Satyanarayana Venkata Ravindra Emani

Christopher Michael Robbins

Ann Verwilst Driscoll

Shivaprasad Lokanath

Vinod Kumar Baikampady Gopalkrishna

Hemant Puri

Ravikumar Gunasekaran

Sandeep Kumar Reddy Venkata

Bkaskar Pemmi

Vedhanabhatla Sarma

A system includes a gas turbine system having a gas turbine engine including a compressor, a combustor, and a turbine. The gas turbine system further includes an exhaust gas recirculation (EGR) system configured to recirculate a first portion of an exhaust flow from the gas turbine engine to an intake of the gas turbine engine. The gas turbine system further includes an exhaust gas injection system, including a multi-stage compressor including a plurality of stages, wherein the multi-stage compressor is configured to compress a second portion of the exhaust flow. The exhaust gas injection system further includes an intercooler coupled to the multi-stage compressor. The exhaust gas injection system is configured to inject the second portion of the exhaust flow into the gas turbine engine at one or more exhaust injection locations other than the intake to provide power augmentation of the gas turbine engine.

System and method for exhaust gas recirculation and injection in gas turbine

A three-way valve for a liquid fuel supply system includes a housing defining a liquid fuel inlet, a purge gas inlet, and at least one drain port. The liquid fuel inlet is sized to receive liquid fuel therethrough for selectively channeling the liquid fuel to a combustor of a gas turbine engine. The purge gas inlet is sized to receive purge gas therethrough for selectively purging liquid fuel from said three-way valve. The at least one drain port is oriented to selectively channel liquid fuel from said three-way valve when purge gas is purging liquid fuel from said three-way valve.

Systems and methods for purging liquid from a liquid fuel supply system

Various embodiments include an offline leak detection system for a turbomachine fuel system. In some embodiments, the leak detection system includes: a fluid supply system fluidly connected to at least one fuel line of the turbomachine, the fluid supply system for delivering a non-flammable fluid to the combustor; a control system operably connected to the fluid supply system, the control system controlling a flow of the non-flammable fluid through the at least one fuel line, and controlling a pressure of the non-flammable fluid in the at least one fuel line to a pressure substantially equal to an operational fuel pressure of the turbomachine; and an optical monitor for determining a presence of the non-flammable fluid on an exterior of the at least one fuel line, the presence of the non-flammable fluid on the exterior of the at least one fuel line indicating a leak.

Gas turbomachine leak detection system and method

A fuel supply system includes a first fuel supply line coupled in flow communication with a first fuel nozzle and configured to channel a first fuel flow to the first nozzle. A second fuel supply line coupled in flow communication with a second fuel nozzle and configured to channel a second fuel flow to the second nozzle. A water supply line coupled in flow communication with a water injection nozzle and configured to channel a water flow to the water injection nozzle. An atomizing fluid supply circuit coupled in flow communication with the first and second fuel supply lines. The atomizing fluid supply circuit configured to channel an atomizing fluid flow to an atomizing nozzle and into atomizing contact with the water flow. The atomizing fluid includes a portion of at least one of the first fuel flow and the second fuel flow.

Fuel supply system for turbine engines and methods of assembling same

In a turbomachine having an inlet, a compressor, and a turbine, a closed loop sends fluid from a stage of the compressor to a heat exchanger in the turbine and to the inlet. The closed loop heats the fluid, cools the turbine, and delivers heated fluid to the inlet. A mixer can be interposed between the heat exchanger and the inlet to mix fluid from the heat exchanger with compressor discharge fluid, delivering the mixed fluid to the inlet. The mixer can control flow received so that desired temperature and/or flow rate can be provided to the inlet.

Turbomachine inlet bleed heating assembly

A system includes a gas turbine engine that includes a turbine section having one or more turbine stages between an upstream end and a downstream end, an exhaust section disposed downstream from the downstream end of the turbine section, and a fluid supply system coupled to the exhaust section. The fluid supply system is configured to route an inert gas to the exhaust section.

System and method for protecting components in a gas turbine engine with exhaust gas recirculation

Embodiments of the present disclosure are directed towards a system that includes a recirculation system. The recirculation system includes a compressor discharge air line extending from a compressor to an air intake. The compressor discharge air line is configured to flow a compressor discharge air flow, and the air intake is configured to supply an air flow to the compressor. An ejector is disposed along the compressor discharge air line between the compressor and the air intake. The ejector is configured to receive and mix the compressor discharge air flow and a turbine exhaust flow to form a first mixture.

Gas turbine anti-icing system

A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy.

Part load performance improvement using deformable bore plugs

The present application provides a combined cycle system. The combined cycle system may include a compressor water wash system in communication with a compressor and a water wash flow, a combustor water injection system in communication with a combustor and an injection flow, and a transient power augmentation system in communication with the compressor, the combustor, and a flow of supplemental water.

Power augmentation systems and methods for grid frequency control

A system for controlling a flow rate of a compressed cooling medium between a compressor section and a turbine section of a gas turbine includes a flow path that is defined between the compressor section and the turbine section of the gas turbine and a thermally actuated variable flow valve disposed within the flow path. The variable flow valve defines an opening that changes in size based on a temperature of the compressed cooling medium flowing therethrough.

System for controlling a cooling flow from a compressor section of a gas turbine

Various embodiments include apparatuses and related methods for determining the enthalpy of steam. In some embodiments, an apparatus includes: an extraction conduit fluidly connected with a steam turbine section, the extraction conduit for obtaining wet steam from the steam turbine section; a mixing chamber fluidly connected with the extraction conduit; an injector fluidly connected with the mixing chamber, the injector for providing dry steam to the mixing chamber for mixing with the wet steam from the steam turbine section to produce a sample mixture; and an enthalpy detection system fluidly connected with the mixing chamber, the enthalpy detection system configured to determine an enthalpy of the sample mixture.

Enthalpy determining apparatus, system and method

A purge system and liquid fuel atomizing system, a system including a purge system and liquid fuel atomizing system, and a method of purging and atomizing are disclosed. The purging involves a first nozzle, a second nozzle, a third nozzle, and a staged compression system having a first stage and a second stage. The first stage is configured to selectively direct a first pressurized fluid stream to the first nozzle and the second nozzle. The second stage is configured to selectively direct a second pressurized fluid stream to the third nozzle.

Purge system, system including a purge system, and purge method

A method for warming the rotor of a gas turbine during extended periods of downtime comprising feeding ambient air to an air blower; extracting compressed air from the air blower; feeding a portion of the compressed air to one side of a heat exchanger and steam (typically saturated) from e.g. a gas turbine heat recovery steam generator; passing the resulting heated air stream from the exchanger into and through into defined flow channels formed within the rotor; continuously monitoring the air temperature inside the rotor; and controlling the amount of air and steam fed to the heat exchanger using a feedback control loop that controls the amount of air and steam feeds to the exchanger and/or adjusts the flow rate of heated air stream into the rotor.

Method for controlling gas turbine rotor temperature during periods of extended downtime

The present application and the resultant patent provide an integrated gasification combined cycle system. The integrated gasification combined cycle system may include a gas turbine engine, one or more power plant components, one or more carbon dioxide compressors, and a vapor absorption chiller. The vapor absorption chiller is driven by a waste heat source flow from the carbon dioxide compressors to produce a chilling medium flow to cool the power plant components.

Integrated gasification combined cycle system with vapor absorption chilling

Disclosed is an optimized approach of using bleed-off of compressed air flow from a gas turbine compressor in a combined-cycle power plant and performance heating to augment plant performance. In one embodiment, a diverted portion of a by-product off gas and the bleed-off of compressed air flow are fired heated to produce a high temperature flue gas that is used to performance heat a pressurized mixture of fuel prior to being supplied to the gas turbine combustor.

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Bengaluru, India

Rajarshi Saha