Abstract
Experiments were conducted in a high-pressure deposition facility to study the effect of engine cycling on the successive buildup of deposits as aircraft shut down and power up. The test facility simulates the pressure and temperature environment of a combustor liner or turbine vane cooling circuit. The coolant flow temperature reaches 894 K (1150 °F) and discharges into a 17-atm (250-psi) cavity pressure at a nominal pressure ratio of 1.027. AFRL05 test dust with a 0- to 10-µm size distribution is added to the coolant gas stream. The cooling circuit consists of a double-walled impingement/effusion cooling plate with nominal hole sizes on the order of 0.5 mm. To simulate cycling, the facility is brought up to the desired operating conditions where the first batch of dust is delivered (2–8 g). The facility is then ramped down to ambient conditions. Following a “dwell” period of approximately 24 h, another batch of dust is delivered once the facility is brought back up to the desired operating condition. Test data were acquired for one, two, and four cycles with different dust masses delivered. Values such as discharge coefficient, pressure ratio, Reynolds number, and temperature are used to evaluate the effects of dust deposition on the impingement/effusion plate setup. Dust capture efficiency is shown to be insensitive to cycling whereas flow blockage is negatively impacted by an increased number of cycles for the same total mass delivered. The sloughing of deposit structures during cooling circuit cool down is postulated to be responsible for the observed behavior.
