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目前正在研制一种用于先进的军用小型燃气涡轮发动机的新型一射流气动喷嘴。这种喷嘴在提高发动机点火性能和燃烧空油气比方面有很大潜力。它有以下三个特点：１）燃烧室中离心式喷嘴和两个气动喷嘴将一体化为一个功能单元；２）最小的燃油通道大于０．４５ｍｍ；３）主流区和喷射流谱的结合和优化显著改善了燃烧空油气比。设计并测试了９个这种喷嘴的研究构型。对有效流区、射角、雾化质量和空气速度进行了测量，并由此判别设计方案的优劣。在环境条件下，对燃烧室前部单喷嘴构型中最佳者进行了点火及贫油熄火测试。最佳喷嘴设计在压降为３１２Ｐａ、每个喷嘴燃油流量为０．６８１ｋｇ／ｈ的情况下仍可点火。
A new one-jet aerodynamic nozzle for advanced military small gas turbine engines is currently being developed. This type of nozzle has great potential for improving engine ignition performance and burning air-to-air ratio. It has the following three characteristics: 1) Centrifugal nozzle in the combustion chamber and two pneumatic nozzles will be integrated into a functional unit; 2) the smallest fuel passage is greater than 0.45mm; 3) the combination of the main zone and the jet stream spectrum Optimization significantly improves the burn-to-air ratio. The study configuration of nine such nozzles was designed and tested. The effective flow area, angle of incidence, atomization mass and air velocity were measured, and the advantages and disadvantages of the design scheme were judged. Under ambient conditions, ignition and lean burnout tests were performed on the best single nozzle configurations in the front of the combustor. The best nozzle design still ignites with a pressure drop of 312 Pa and a fuel flow rate of 0.681 kg / h per nozzle.