Purpose

The lean blowout (LBO) limit of the combustor is one of the important performance parameters for any gas turbine combustor design. This study aims to predict the LBO limits of an in-house designed swirl stabilized 3kW can-type micro gas turbine combustor.

Design/methodology/approach

The experimental prediction of LBO limits was performed on 3kW swirl stabilized combustor fueled with methane for the combustor inlet velocity ranging from 1.70 m/s to 6.80 m/s. The numerical prediction of LBO limits of combustor was performed on two-dimensional axisymmetric model. The blowout limits of combustor were predicted through calculated average exit gas temperature (AEGT) method and compared with experimental predictions.

Findings

The results show that the predicted LBO equivalence ratio decreases gradually with an increase in combustor inlet velocity.

Practical implications

This LBO limits predictions will use to fix the operating boundary conditions of 3kW can-type micro gas turbine combustor. This methodology will be used in design stage as well as in the testing stage of the combustor.

Originality/value

This is a first effort to predict the LBO limits on micro gas turbine combustor through AEGT method. The maximum uncertainty in LBO limit prediction with AEGT is 6 % in comparison with experimental results.

中文翻译：

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微型燃气轮机燃烧室稀燃极限的实验与数值预测

目的

燃烧器的稀燃 (LBO) 极限是任何燃气轮机燃烧器设计的重要性能参数之一。本研究旨在预测内部设计的涡流稳定 3kW 罐式微型燃气轮机燃烧器的 LBO 极限。

设计/方法/方法

LBO 极限的实验预测是在以甲烷为燃料的 3kW 涡流稳定燃烧器上进行的，燃烧器入口速度范围为 1.70 m/s 至 6.80 m/s。燃烧室LBO极限的数值预测是在二维轴对称模型上进行的。通过计算平均出口气体温度（AEGT）方法预测燃烧器的井喷极限，并与实验预测进行比较。

发现

结果表明，随着燃烧室入口速度的增加，预测的LBO当量比逐渐降低。

实际影响

该 LBO 限制预测将用于确定 3kW 罐式微型燃气轮机燃烧器的运行边界条件。该方法将用于设计阶段以及燃烧器的测试阶段。

原创性/价值

这是通过AEGT方法预测微型燃气轮机燃烧室LBO极限的首次尝试。与实验结果相比，使用 AEGT 进行 LBO 极限预测的最大不确定性为 6%。