The experimental investigation of the operational characteristics of fuel nozzle for a heavy gas turbine was performed.
对某重型燃气轮机燃料喷嘴的工作特性进行了试验研究。
The invention relates to a gas turbine premixer with internal cooling. A system that includes a turbine fuel nozzle (144) comprising an air-fuel premixer (170).
本发明涉及具有内冷却的燃气涡轮机预混合器，具体而言，一种系统包括含有空气-燃料预混合器（170）的涡轮燃料喷嘴（144）。
The effects of nozzle structure, fuel gas injection velocity and excess air coefficient on NOx emission in high temperature air combustion were investigated.
通过两种结构烧嘴的热态燃烧试验对比，研究了烧嘴结构、燃气射流速度、过量空气系数对高温空气燃烧过程氮氧化物排放的影响特性。
The effects of nozzle structure, fuel gas injection velocity and excess air coefficient on NOx emission in high temperature air combustion were investigated.
通过两种结构烧嘴的热态燃烧试验对比，研究了烧嘴结构、燃气射流速度、过量空气系数对高温空气燃烧过程氮氧化物排放的影响特性。
应用推荐