General Electric Company

Nan Zong

Pradeep Naik

Kwanwoo Kim

Fei Han

Kapil Kumar Singh

Mark Anthony Mueller

Anthony Wayne Krull

Jeffrey Michael Martini

Shiva Kumar Srinivasan

Gerardo Antonio Salazar Lois

Steven Keith Handelsman

Ahmed Mostafa ELKady

Qingguo Zhang

Rishikesh Prakash Karande

Danielle Marie Kalitan

Preetham Balasubramanyam

Richard Bradford Hook, Jr

Ahmed Mostafa El Kady

Ahmed A Abdel-Hafez

A system including an annular combustor having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine. The system also includes a supply passage configured to supply a fluid flow from a compressor to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.

System and method having annular flow path architecture

A fuel-air mixer for use with a combustor is provided. The fuel-air mixer includes an outer ring, an intermediate hub disposed coaxially within the outer ring such that a first plenum is formed therebetween, and an inner hub disposed coaxially within the intermediate hub such that a second plenum is formed therebetween. A first swirler including a plurality of first swirler vanes is positioned between the outer ring and the intermediate hub, wherein the first swirler is configured to rotate fluid flowing therethrough in a first direction. A second swirler including a plurality of second swirler vanes is positioned between the intermediate hub and the inner hub, wherein the second swirler is configured to rotate fluid flowing therethrough in a second direction. A plurality of fuel injection conduits are also defined within the fuel-air mixer for channeling fuel to the first and second plenums.

Fuel-air mixer for use with a combustor assembly

A system is disclosed that includes a combustor having an end cover and at least one fuel nozzle assembly extending from an inner face of the end cover. A cartridge may extend through the end cover and into the fuel nozzle assembly. The cartridge may define an opening for receiving light emitted from within the combustor. Additionally, a fiber optic cable may be disposed within the cartridge and may be configured to capture at least a portion of the light received through the opening.

System and method for controlling combustor operating conditions based on flame detection

A gas turbine engine control system comprises a data acquisition and analysis system for receiving a signal from a combustion dynamics sensor and providing an output signal and a combustion dynamics control system for controlling combustion dynamics based on the output signal. The control system is associated with a purge-air flow and comprises an acoustic driver, or a flow-manipulating device, or both to perturb the purge-air flow entering the combustor can for controlling combustion dynamics.

Gas turbine combustion dynamics control system and method

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Nan Zong