Fuel nozzle for a turbine engine combustor

A fuel nozzle comprising:

• a fuel nozzle body having a central channel defining a channel centerline, the central channel opening at a fuel nozzle outlet;
• a set of fuel jets extending through the fuel nozzle body and fluidly coupled to the central channel to define an injecting section of the central channel;
• a compressed air resonator provided within the central channel and defining a resonating section of the central channel, the compressed air resonator configured to receive a portion of a flow of compressed air and generate pressure waves that are emitted into the central channel through a resonator orifice of the compressed air resonator that opens directly into the central channel within the fuel nozzle body and axially upstream of where the set of fuel jets open to the central channel, wherein the pressure waves include a frequency of greater than or equal to 400 Hertz and less than or equal to 5000 Hertz;
• a first compressed air inlet formed through the fuel nozzle body and opening into a portion of the central channel exterior to the compressed air resonator;
• and
• a second compressed air inlet formed through the fuel nozzle body and opening into the compressed air resonator, the second compressed air inlet being structurally and fluidly separate from the first compressed air inlet.

A fuel nozzle for a combustion section having a combustion chamber, the fuel nozzle comprising:

• a fuel nozzle body having a central channel defining a channel centerline, the central channel opening at a fuel nozzle outlet, the fuel nozzle outlet opening into the combustion chamber;
• a set of fuel jets extending through the fuel nozzle body and fluidly coupled to the central channel to define an injecting section of the central channel;
• a compressed air resonator provided within the central channel and defining a resonating section of the central channel, the compressed air resonator configured to receive a portion of a flow of compressed air and generate pressure waves that are emitted into the central channel through a resonator orifice of the compressed air resonator that opens directly into the central channel within the fuel nozzle body and axially upstream of where the set of fuel jets open to the central channel;
• a swirler section located radially outward from the resonating section, with respect to the channel centerline;
• a first compressed air inlet formed through the fuel nozzle body and opening into a portion of the central channel exterior to the compressed air resonator;
• and
• a second compressed air inlet formed through the fuel nozzle body and opening into the compressed air resonator, the second compressed air inlet being structurally and fluidly separate from the first compressed air inlet.