General Electric Company

Ge Infrastructure Technology, LLC

Ge Vernova Technology Gmbh

Jeevankumar Krishnan

Rajarshi Saha

Laxmikant Merchant

Paul Burchell Glaser

Anil Kumar Dasoji

Baha Mahmoud Suleiman

Avishetti Srinivas

Rajesh K Reddy

Ravikumar Gunasekaran

Sandeep Kumar Reddy Venkata

Hatem Mohamed Mohyeldin Ibrahim Selim

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

A foundation temperature control system for use with a rotary machine is positioned between the rotary machine and a foundation. The foundation temperature control system includes a heat shield, an insulation pack positioned below the heat shield, and an air gap at least partially defined by the heat shield and the insulation pack. The heat shield, the insulation pack, and the air gap are oriented to facilitate maintaining a temperature of the foundation supporting the rotary machine below a maximum rated operating temperature of the foundation.

Systems and methods for controlling temperature in a supporting foundation used with a gas turbine engine

In a one embodiment, a gas turbine system that includes a first pump that supplies distillate fuel to a combustor. A second pump that supplies fuel oil to the combustor. A fuel selection unit that controls a first flow of distillate fuel and a second flow of fuel oil to the combustor. A controller that receives feedback from a sensor and in response to the feedback from the sensor controls the fuel selection unit to start the gas turbine system on the fuel oil.

Gas turbine fuel system

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Bengaluru, India

Jeevankumar Krishnan