FORECASTING NONUNIFORMITY OF GAS TEMPERATURE FIELD AT THE GAS TURBINE ENGINE COMBUSTOR OUTLET IN THE CASE OF INDEFINITENESS OF INITIAL CONDITIONS OF ATOMIZED FUEL SUPPLY

Omair Alhatim

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FORECASTING NONUNIFORMITY OF GAS TEMPERATURE FIELD AT THE GAS TURBINE ENGINE COMBUSTOR OUTLET IN THE CASE OF INDEFINITENESS OF INITIAL CONDITIONS OF ATOMIZED FUEL SUPPLY

机译：在原子化燃料供应初始条件不足的情况下预测燃气轮机发动机燃烧室出口气体温度场的不均匀性

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The influence of the initial conditions in modeling an atomized fuel on the accuracy of evaluating the gas temperature field nonuniformity at the helicopter gas turbine engine annular reverse flow combustor outlet is investigated based on the numerical solution of the problem of combustion two-phase three-dimensional flow. Calculations of four fuel droplet supply models are performed based on the integration of the Reynolds equations for the gas phase and the Lagrange equations for the droplet phase. A slight impact of the initial conditions on the gas temperature field nonuniformity at the combustor outlet is revealed. Comparison of the calculation results and experimental data shows that they are better reconciled in relation to radial nonuniformity than in relation to circumferential one.

机译：基于燃烧两相三维问题的数值解，研究了雾化燃料建模的初始条件对直升机燃气涡轮发动机环形逆流燃烧室出口处气体温度场不均匀性评估准确性的影响。流。基于气相的雷诺方程和液滴相的拉格朗日方程的积分，对四个燃料滴供应模型进行了计算。揭示了初始条件对燃烧器出口处气体温度场不均匀性的轻微影响。计算结果和实验数据的比较表明，相对于径向不均匀性，其相对于圆周不均匀性更好。

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来源
《High Temperature Material Processes》 |2016年第1期|共10页
作者
Omair Alhatim;
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原文格式 PDF
正文语种 eng
中图分类计量学;
关键词
gas turbine engine; combustor; flow; combustion; fuel droplets; numerical modeling; initial conditions; gas temperature field;

机译：燃气轮机;燃烧器;流量;燃烧;燃料滴;数值模拟;初始条件;气体温度场;

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1. FORECASTING NONUNIFORMITY OF GAS TEMPERATURE FIELD AT THE GAS TURBINE ENGINE COMBUSTOR OUTLET IN THE CASE OF INDEFINITENESS OF INITIAL CONDITIONS OF ATOMIZED FUEL SUPPLY [J] . Omair Alhatim High Temperature Material Processes . 2016,第1期

机译：在原子化燃料供应初始条件不足的情况下预测燃气轮机发动机燃烧室出口气体温度场的不均匀性
2. Influence of combustor inlet condition on combustor exit gas peak temperature factor (experiment by using the combustor with pressure atomizing fuel nozzles and the combustor with airblast type fuel injectors) [J] . Sato Yukinori, Toh Hidemi, Watanabe Takeshi, 日本ガスタ-ビン学会誌 . 2001,第1期

机译：燃烧室入口条件对燃烧室出口气体峰值温度系数的影响（通过使用带有压力雾化燃料喷嘴的燃烧室和带有鼓风型燃料喷射器的燃烧室进行的实验）
3. Influence of combustor inlet condition on combustor exit gas peak temperature factor (experiment by using the combustor with pressure atomizing fuel nozzles and the combustor with airblast type fuel injectors) [J] . Sato Yukinori, Toh Hidemi, Watanabe Takeshi, 日本ガスタ-ビン学会誌 . 2001,第1期

机译：燃烧器入口条件对燃烧器出口气峰温度因子的影响（用压力氧气喷嘴用燃烧器和空燃型燃料喷射器的试验）
4. Numerical investigations of methane fueled oxy-fuel combustion model in a gas turbine combustor 1. Flow fields, temperature, and species distribution 2. Effect of CO_2 recirculation [C] . M. A. NEMITALLAH, R. BEN-MANSOUR, M. A. HABIB Advances in fluid mechanics amp; heat amp; mass transfer . 2012

机译：燃气轮机燃烧室中以甲烷为燃料的氧-燃料燃烧模型的数值研究1.流场，温度和物质分布2. CO_2再循环的影响
5. Experimental Investigation of the Effect of Engine Representative Combustor Exit Temperature Profile and Disc Cavity Leakage Flow on the Film Cooling of Contoured Hub Endwall of a High Pressure Gas Turbine Rotor Cascade. [D] . Ayaskanta, Arya. 2013

机译：发动机代表性燃烧室出口温度曲线和圆盘腔泄漏流对高压燃气轮机转子叶栅轮廓轮毂端壁薄膜冷却影响的实验研究。
6. The Effect of Partial Premixing and Heat Loss on the Reacting Flow Field Prediction of a Swirl Stabilized Gas Turbine Model Combustor [O] . Simon Gövert, Daniel Mira, Jim B. W. Kok, -1

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7. Development of a 1300.DEG.C.-Class Gas Turbine Combustor Burning Coal-Derived Low-BTU Gaseous Fuels. 4th Report. Experimental Evaluation of an Advanced Rich-Lean Combustor under High-Pressure Conditions. [O] . Toshihiko NAKATA, Mikio SATO, Toru NINOMIYA, 1992

机译：开发1300.deg.c.-Class燃气轮机燃烧器燃烧煤衍生的低BTU气体燃料。第四次报告。高压条件下先进富益燃烧器的实验评价。
8. High-Temperature Turbine-Technology Program. Phase II. Technology Test and Support Studies. Design and Development of a Regeneratively Fuel Cooled High Temperature Gas Turbine Combustor for Operation on Low Btu Gas [R] . Dobson, R. L., Kwan, T. C., Straume, T. 1982

机译：高温涡轮技术计划。第二阶段。技术测试和支持研究。低Btu气体下蓄热式高温燃气轮机燃烧器的设计与开发

FORECASTING NONUNIFORMITY OF GAS TEMPERATURE FIELD AT THE GAS TURBINE ENGINE COMBUSTOR OUTLET IN THE CASE OF INDEFINITENESS OF INITIAL CONDITIONS OF ATOMIZED FUEL SUPPLY

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