Experimental Study on Blowout Characteristics of Aeroengine Combustor under High Altitude Low Pressure and Low Temperature Condition

Flameout at high altitude is a serious security threat for the aircraft engine. Stable combustion and reliable reignition at high altitude are basic requirements for the combustor of the aircraft engine. The design and debugging results of the simulated altitude test facility (TSATF) were introduced in this paper. The simulation of high-altitude condition from ground state to 10 km was realized by TSATF. Results show that the fuel-air-ratio (FAR) of lean blow-out (LBO) limit rises with the mcrease of simulation altitude. The FAR of the LBO limit at ground state was 0.016. The FAR of the LBO limit at 10 km was 0.071, which increased three times than ground state. At low-temperature and low-pressure environment, the position of flame front decreased continuously. The area of heat released from combustion was limited near the fuel nozzle with the luminous intensity of CH^* decreasing continuously. The flame in the combustor began to show light blue at the simulation altitude of 4 km, and turned to light blue completely at the simulation altitude of 10 km meaning that. Then the combustion tended to be unstable.