SYSTEMS AND METHODS FOR A FUEL PRESSURE OSCILLATION DEVICE FOR REDUCTION OF COHERENCE

摘要

A system with a gas turbine engine is provided. The gas turbine engine includes a first combustor comprising a first fuel nozzle, a second combustor comprising a second fuel nozzle, and a first fuel pressure oscillation system. The first fuel pressure oscillation system includes a first rotary device coupled to a first fuel circuit. The first fuel circuit is disposed along a first fuel passage leading to the first fuel nozzle. The first rotary device is configured to generate a first fuel pressure oscillation through the first fuel nozzle. The gas turbine engine also includes a second fuel pressure oscillation system having a second rotary device coupled to a second fuel circuit. The second fuel circuit is disposed along a second fuel passage leading to the second fuel nozzle, and the second rotary device is configured to generate a second fuel pressure oscillation through the second fuel nozzle.

主权项

1. A system, comprising:
a gas turbine engine, comprising:
a first combustor comprising a first fuel nozzle;a second combustor comprising a second fuel nozzle;a first fuel pressure oscillation system having a first rotary device coupled to a first fuel circuit, wherein the first fuel circuit is disposed along a first fuel passage leading to the first fuel nozzle, and wherein the first rotary device is configured to generate a first fuel pressure oscillation within the first fuel nozzle; anda second fuel pressure oscillation system having a second rotary device coupled to a second fuel circuit, wherein the second fuel circuit is disposed along a second fuel passage leading to the second fuel nozzle, and wherein the second rotary device is configured to generate a second fuel pressure oscillation within the second fuel nozzle.