CAJ | 학술논문

为研究液体在透平叶栅流道内雾化特性，在直流道和折转角分别为30°、60°的叶栅流道内进行了液体横向射流雾化试验，试验来流速度为56~91m/s，喷嘴压差为50~400 kPa ，采用喷油杆结构布置在叶片前缘喷射燃料，用Fraunhofer 衍射技术测量液滴雾化细度，用CCD相机记录流道内液滴射流轨迹。研究发现：透平叶栅流道内液滴轨迹同时受液气动量比、叶片折转角度的影响，在叶片前缘向吸力面侧喷和逆喷时的雾化效果优于直流道内横向侧喷。喷嘴压差大于400 kPa时，向叶片吸力面侧喷的液滴索泰尔平均直径小于30μm，雾化粒径可满足燃气轮机燃烧室的要求。
위연구액체재투평협책류도내무화특성，재직류도화절전각분별위30°、60°적협책류도내진행료액체횡향사류무화시험，시험래류속도위56~91m/s，분취압차위50~400 kPa ，채용분유간결구포치재협편전연분사연료，용Fraunhofer 연사기술측량액적무화세도，용CCD상궤기록류도내액적사류궤적。연구발현：투평협책류도내액적궤적동시수액기동량비、협편절전각도적영향，재협편전연향흡력면측분화역분시적무화효과우우직류도내횡향측분。분취압차대우400 kPa시，향협편흡력면측분적액적색태이평균직경소우30μm，무화립경가만족연기륜궤연소실적요구。
In order to research the liquid fuel spray characteristics in turbine cascade passage, experiment was focused on straight channel and cascade channel with different turning angle (30 degree and 60 degree). The inlet velocity in experiment varied from 56m/s to 91m/s and the injector pressure difference varied from 50kPa to 400 kPa. Fuel injector was injected at blade leading edge in turbine cascade channel. Fraunhofer diffraction technique was used to measure droplet diameter, and the spray trajectory was recorded by CCD camera. The result shows that spray trajectory in turbine cascade passage is influenced by liquid-air momentum ratio as well as blade turning angle. Reverse jet and lateral jet to suction surface at leading edge in cascade channel have better atomization effect than lateral jet in straight channel. Injecting to blade suction surface have a Sauter mean diameter less than 30μm when the nozzle pressure is greater than 400 kPa, the atomizing fineness can meet the requirements of gas turbine combustor.