模型燃气轮机中OH自由基的平面激光诱导荧光检测方案(气体流量计)

Modern gas turbine engines are typically operated in a lean-premixed configuration in order to meet emissions requirements. Lean operation makes gas turbines more susceptible to combustion instability, which can cause catastrophic hardware failure if left unchecked. The spatially uneven distribution of fuel in a gas turbine combustor, known as fuel staging, is an effective way of suppressing instabilities. This dissertation examines the effect of both steady-state and transient fuel-staging in a model gas turbine combustor. First, the steady-state effect of fuel staging on nominally unstable operating conditions is examined. At 200 degrees Celsius and a bulk flow velocity of 26 m/s, the combustor undergoes self-excited instabilities when the equivalence ratio is between  = 0.70 and  = 0.74 when all nozzles are fueled equally. These instabilities are suppressed when the center nozzle equivalence ratio is increased to Staging = 0.85 and the outer nozzle equivalence ratio maintained at  = 0.70or when the global equivalence ratio is maintained at  = 0.70 by increasing the center nozzle equivalence ratio to Staging = 0.74 and decreasing the outer nozzle equivalence ratio to Staging = 0.69. The staged p0 RMS amplitudes are found to decrease with increasing equivalence ratio and the damping rates found to increase with increasing equivalence ratio.