Study on aerodynamic characteristics computation method for turbine considering component effects
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摘要:
为研究现有燃气轮机改烧氢混燃料时的涡轮气动特性变化，推荐了一种涡轮气动特性参数定义方法，其中折合流量和折合转速的定义考虑了燃气工质物性的变化。以LM2500+SAC航改燃气轮机的高压涡轮和动力涡轮为例，其高压涡轮为2级轴流式气冷涡轮，动力涡轮为6级轴流式无冷却涡轮，采用基于单通道RANS（Reynolds averaged Navier-Stokes）方程求解的三维数值模拟方法，分别计算了烧天然气燃料场景下的涡轮气动特性及烧氢混燃料场景下的涡轮气动特性，并对比分析了两者之间的变化关系。结果表明：利用推荐的涡轮气动特性参数定义，可以统一两种燃料的涡轮特性曲线（同一折合转速和膨胀比下的折合流量相差在0.2%以内）。这说明在已知天然气工质的涡轮工作特性时，可以直接换算出氢混燃料涡轮的工作特性，这为涡轮气动特性数据的推广应用提供了方便。
Abstract:In order to study the turbine aerodynamic characteristic variation when the fuel changed from natural gas to mixed-hydrogen fuel, an aerodynamic characteristic definition for turbine was given, in which the definition of corrected mass flow and corrected rotation speed can integrated the gas property variation. The turbine aerodynamic characteristics 2-stage cooled high pressure turbine and 6-stage uncooled power turbine of LM2500+SAC gas turbine was investigated based on the RANS (Reynolds averaged Navier-Stokes) simulation method and the new characteristic definitions. Also, the fuels variations from natural gas fuel to mixed-hydrogen fuel are studied. The results shows that, the two work characteristic curves can be classified using recommended aerodynamic parameters definition (the corrected mass-flow distinction between the two fuels was under 0.2% at the same corrected rotating speed and total pressure ratio conditions), and it was indicated that the real turbine aerodynamic characteristic of mixed-hydrogen fuel could be gotten from the turbine aerodynamic characteristic of original natural gas fuel using the characteristic definition. This provides convenience for the application turbine aerodynamic characteristic data.
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Key words:
- gas turbine /
- cooled turbine /
- aerodynamic characteristic /
- corrected mass flow /
- turbine efficiency
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图 1 气冷涡轮总-总效率定义示意图
Figure 1. Schematic diagram of total-total efficiency definition for cooled turbine
图 2 LM2500+SAC燃机高压涡轮引气示意图
Figure 2. Schematic diagram of LM2500+SAC high pressure turbine secondary flow
图 6 常规定义下折合流量随膨胀比的变化（高压涡轮）
Figure 6. Corrected mass flow with traditional definition vs. expansion ratio （high pressure turbine）
图 7 常规定义下总-总效率随膨胀比的变化（高压涡轮）
Figure 7. Total-total efficiency with traditional definition vs. expansion ratio （high pressure turbine）
图 8 推荐定义下折合流量随膨胀比的变化（高压涡轮）
Figure 8. Corrected mass flow with recommended definition vs. expansion ratio （high pressure turbine）
图 9 推荐定义下总-总效率随膨胀比的变化（高压涡轮）
Figure 9. Total-total efficiency with recommended definition vs. expansion ratio （high pressure turbine）
图 11 常规定义下折合流量随膨胀比的变化（动力涡轮）
Figure 11. Corrected mass flow with traditional definition vs. expansion ratio （power turbine）
图 12 常规定义下总-总效率随膨胀比的变化（动力涡轮）
Figure 12. Total-total efficiency with traditional definition vs. expansion ratio （power turbine）
图 13 推荐定义下折合流量随膨胀比的变化（动力涡轮）
Figure 13. corrected mass flow with recommended definition vs. expansion ratio （power turbine）
图 14 推荐定义下总-总效率随膨胀比的变化（动力涡轮）
Figure 14. Total-total efficiency with recommended definition vs expansion ratio （power turbine）
表 1 效率计算过程参数
Table 1. Efficiency computation process parameters
引气位置 质量流量/（kg/s） 总温/K 总压/kPa 焓/（kJ/kg） 主流 67.89 1638.0 2191 1927.67 冷气EI1+ EI2 8.27 774.5 2301 836.54 EI3 3.44 774.5 2301 836.54 EI4 1.38 774.5 2301 836.54 冷气EA 2.07 645.4 1512 686.73 ISO 82.67 1487.5 1728.52 实际出口 82.67 1094.9 475 1224.50 理想出口 82.67 1048.0 1166.20 
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表 2 涡轮特性参数定义
Table 2. Parameter definition for turbine performance
参数 常规定义 推荐定义1
（用于无冷却涡轮）推荐定义2
（用于冷却涡轮）折合流量 $ {G}_{1}^{*}=G\sqrt{{T}_{\mathrm{t},1}}/{p}_{\mathrm{t},1} $ $ {G}_{2}^{*}=G\sqrt{R{T}_{t,1}}/{p}_{\mathrm{t},1} $ $ {G}_{3}^{*}={G}_{2}\sqrt{{R}_{2}{T}_{\mathrm{I}\mathrm{S}\mathrm{O}}}/{p}_{\mathrm{t},1} $ 折合转速 $ {n}_{1}^{*}=n/\sqrt{{T}_{\mathrm{t},1}} $ $ {n}_{2}^{*}=n/\sqrt{R{T}_{\mathrm{t},1}} $ $ {n}_{3}^{*}=n/\sqrt{{R}_{2}{T}_{\mathrm{I}\mathrm{S}\mathrm{O}}} $
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表 3 燃气组分摩尔分数
Table 3. Molar fraction of gas composition
燃料类型 组分摩尔分数/% N2 O2 CO2 H2O AR（氩气） SO2 天燃气（NG） 74.44 10.81 4.65 9.22 0.88 0 氢混燃料
（75%H2+25%NG）72.51 10.90 2.49 13.23 0.86 0
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