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中文摘要: 针对燃气轮机双燃料喷嘴气体燃料路，采用Fluent仿真分析双燃料喷嘴气体燃料路孔径、布置及喷射 角度对燃烧室性能的影响，研究结果表明:对于本型双燃料喷嘴气体燃料路，孔径1. 8 mm非均匀5组布置、 喷射角度为60°时燃烧室性能最优;喷射孔径从1.5 mm增大至3. 3 mm,会导致高温区径向上向火焰筒近壁 区发展，火焰筒壁温上升，出口温度场转好，出口平均温度下降;燃料喷射锥角从60°增大至80 ℃，燃烧室性能 变化规律与孔径增大时类似;但喷射角度带来的燃烧室性能变化没有气体燃料喷口布置变化带来的性能影 响大。当结构限制孔径尺寸时，可以采用非均布布置方法，即“几个一组”的方式进行布置，可在结构限制条 件下取得较好的燃烧室性能。
Abstract:In this paper，Fluent software was used to simulate and analyze the relationship between the performance of the combustion
chamber and the diameter， layout， injection angle of the dual-fuel nozzle gas hole. The research results showed that: combustion
chamber performance was best when the injection hole diameter was 1.8 mm，the injection angle was 60° and the hole arranged for five
groups in pairs. High-temperature zone changed the location to the near wall area of the liner at the radial direction， the wall temperature of the liner raised，the outlet temperature field turned better，and the average outlet temperature decreased when the hole diameter increased from 1.5 to 3. 3 mm. When the angle of fuel injection increased from 60° to 80°，the performance of tlie combustion
chamber is similar to that when the hole diameter increased. However， the change of combustion chamber performance caused by injection angle is less significant than that caused by the change of nozzle hole diameter. When the structure restricts the nozzle hole size，the method of heterogeneous arrangement can be adopted and got the combustion chamber performance.
文章编号： 中图分类号：TK470.30 文献标志码：
基金项目:
| 作者 | 单位 |
| 徐海成 | 海军装备部装备项目管理中心 |
| 徐文燕 | 中国船舶集团第七〇三研究所 船舶与海洋工程动力系统国家工程实验室— 海洋工程燃气轮机实验室 |
| 杨 强 | 中国船舶集团第七〇三研究所 船舶与海洋工程动力系统国家工程实验室— 海洋工程燃气轮机实验室 |
| 李名家 | 中国船舶集团第七〇三研究所 船舶与海洋工程动力系统国家工程实验室— 海洋工程燃气轮机实验室 |
引用文本：
作者.题名[J].刊名,出版年份,卷号(期号):起止页码.
[2]KIM K M, PARK J S, DONG H L, et al. Analysis of conjugated heat transfer, stress and failure in a gas turbine blade with circular cooling passages[J]. Engineering Failure Analysis, 2011, 18(4):1212-1222.
作者.题名[J].刊名,出版年份,卷号(期号):起止页码.
[2]KIM K M, PARK J S, DONG H L, et al. Analysis of conjugated heat transfer, stress and failure in a gas turbine blade with circular cooling passages[J]. Engineering Failure Analysis, 2011, 18(4):1212-1222.