General Electric Company

General Electric Technology Gmbh

Abhijit Prabhakar Kulkarni

Predrag Popovic

Douglas Edward Dean

Derrick Walter Simons

Alan Meier Truesdale

Arvind Venugopal Menon

Scott Arthur Day

Timothy Andrew Healy

James Harper

John Rogers Huey

Kevin Wood Wilkes

Carey Edward Romoser

Mihir Kumar Lal

Akilezkrishnamurthy Arthanari

A method of detecting flame state of a combustor of a turbine engine. The method includes determining at least one of a first derivative and a second derivative of a compressor discharge pressure of a compressor of the turbine engine; determining at least one of a first derivative and a second derivative of a gas turbine exhaust gas temperature of the exhaust gases output by the turbine engine; determining at least one of a first derivative and a second derivative of a gas turbine shaft/rotor speed of the turbine engine; determining at least one of a first derivative and a second derivative of combustor dynamic pressure monitoring; and determining a flame state of a combustor of the turbine engine based on the combustor dynamic pressure monitoring, the determined derivatives of the combustion dynamics, compressor discharge pressure, gas turbine shaft/rotor speed, and gas turbine exhaust gas temperature of the exhaust gases.

Non-optical flame detector and method for a combustor of a turbine engine

This disclosure relates to systems and methods for tuning combustion dynamics in a combustor. In one embodiment of the disclosure, a method includes providing, via at least one sensor, combustion dynamics amplitude data associated with a combustor. Method may allow monitoring, by an equipment controller communicatively coupled to the at least one sensor, the combustion dynamics amplitude data. The method may allow detecting at least one change in acoustic pressure amplitude associated with combustion in the combustor. In response to detecting the change in the acoustic pressure amplitude, the method proceeds with determining a fuel split change to at least two fuel circuits configured to supply fuel to the combustor, and applying the fuel split change to the combustor.

Model-less combustion dynamics autotune

A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured operating parameter of the combustor.

System and method for controlled fuel blending in gas turbines

A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured composition of the first fuel.

System and method for fuel blending and control in gas turbines

Embodiments of the invention can provide systems and methods for determining a target exhaust temperature for gas turbines. In one embodiment of the disclosure, there is disclosed a method for determining a target exhaust temperature for a gas turbine. The method can include determining a target exhaust temperature based at least in part on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based at least in part on steam humidity; and changing the target exhaust temperature based at least in part on the temperature adjustment.

Systems and methods for determining a target exhaust temperature for a gas turbine

A gas turbine comprises a plurality of target exhaust temperature determination modules, the plurality of target exhaust temperature modules comprising a nitrogen oxide (NOx) compliance module configured to determine an exhaust temperature at which an exhaust of the gas turbine complies with a maximum permitted level of NOx; at least one bias module, the at least one bias module configured to apply a bias to an output of at least one of the plurality of target exhaust temperature determination modules; and a controller configured to operate the gas turbine to produce the exhaust temperature determined by the NOx compliance module.

Growing community of inventors

Hyderabad Telangana, India

Abhijit Prabhakar Kulkarni