航空活塞发动机用自增压喷嘴喷雾特性试验

For the better application of the self-pressurized injector on aircraft piston engines, the spray characteristics of a self-pressurized injector was experimentally studied in a constant-volume vessel. Spray characteristics of RP-3 aviation kerosene under different ambient pressure, fuel temperature and ambient temperature were studied using visualization technology combining Matlab image processing program. Result showed that, the surface waves and fuel strings can be observed obviously under the ambient pressure of 0.1MPa. With the ambient pressure increasing from 0.1MPa to 0.8MPa, the typical hollow cone spray was transformed into a hollow cone spray with large scale vortexes. The maximum spray penetration reduced by 45%, and the maximum spray area reduced by 55.3%, respectively. The increase of fuel temperature promotes spray evaporation to facilitate cold start. The spray penetration, area and cone angle were all minimum when the fuel temperature was 50℃. At the ambient pressure of 0.1MPa, the spray penetration and area increased at first and then decreased with the increase of ambient temperature. The maximum spray penetration reached 67.3mm at ambient temperature of 60℃, the maximum spray area reached 915.5mm² at ambient temperature of 50℃, respectively. The spray cone angle decreased with the increasing of ambient temperature, reaching the minimum value of 9.2° at ambient temperature of 90℃.