Experiment on combustion characteristics of micro gas turbine combustor

被引：0

作者：

Liu A. ^{[1
]}

Li Y. ^{[1
]}

Yang Y. ^{[1
]}

Zeng W. ^{[1
]}

Liu K. ^{[1
]}

机构：

[1] Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System, School of Aero-Engine, Shenyang Aerospace University, Shenyang, 110136, Liaoning

来源：

| 1600年 / BUAA Press卷 / 35期

关键词：

Combustion characteristics; Emission characteristics; Equivalent ratio; Fuel distribution ratio; Micro gas turbine;

D O I：

10.13224/j.cnki.jasp.2020.06.024

中图分类号：

学科分类号：

摘要：

According to the requirements of low pollution emission of gas turbine, the combustion characteristic experiment was carried out on the single head experiment piece of the combustor of low emission micro gas turbine designed for the use of gas fuel. The position and quantity of the fuel nozzle, the fuel distribution ratio between the duty class and the main combustion stage, and the combustion efficiency and pollutant emission characteristics under different air flow distribution modes were compared and analyzed. Results showed that changing the position and quantity of the fuel nozzle can change the mixing characteristics of the fuel and air, yielding a great effect on the combustion characteristics; the change of the fuel flow distribution ratio between the duty class and the main combustion stage led to the change of the equivalence ratio of each combustion zone, and the reduction of the current ratio of the main combustion stage to below 0.8 was conducive to the reduction of pollutant emissions; the change of air flow distribution ratio of the combustion chamber was conducive to the reduction of pollutant emissions With this method, the equivalence ratio of the main combustion zone can be reduced, the NOx emission can be reduced to 27.2mg/m3, and the combustion efficiency can reach 98.6%. However, the decrease of air flow rate for mixing could increase the outlet temperature distribution coefficient from 0.21 to 0.24. © 2020, Editorial Department of Journal of Aerospace Power. All right reserved.

引用

页码：1335 / 1344

页数：9

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