多级透平试验模化准则研究

石䶮; 周晟鋆; 黄单; 彭生红

doi:10.13224/j.cnki.jasp.20240143

多级透平试验模化准则研究

doi: 10.13224/j.cnki.jasp.20240143

国家电力投资集团有限公司中国联合重型燃气轮机技术有限公司，上海 200131

详细信息

作者简介:
石䶮（1983-），男，高级工程师，博士，主要从事重型燃气轮机透平气动设计与试验技术研究。E-mail：shiyan@spic.com.cn

通讯作者:
彭生红（1978-），男，研究员，博士生，主要从事重型燃气轮机叶轮机试验技术研究。E-mail：psh-305@163.com

中图分类号: V231.1
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出版历程
- 收稿日期: 2024-03-13
- 网络出版日期: 2024-05-07

Investigation on test modeling criteria for multistage turbine

China United Gas Turbine Technology Company Limited，State Power Investment Corporation，Shanghai 200131，China

摘要

摘要:
为提升多级透平中温模化试验的流场相似性，构建并校验了两级透平三维数值模型，定量研究试验模化准则选取对流场相似性的影响，提出了一种调整工质比热比的新方法。结果表明：中温模化条件下的工质比热比与设计值不相等，导致多级透平流场相似性沿流动方向逐渐下降；保证膨胀比模化准则时，末级透平动叶气动载荷系数降低4.78%，出口气流角偏差达3°～5°；保证折合功率模化准则时，末级透平折合转速偏大1.29%，动叶气膜冷气出流背压下降2.5%～6.5%；将空气燃烧转变为燃气再与水蒸气掺混，可以得到与不同等级重型燃气轮机真实燃气比热比相等的试验工质；在中温试验条件下使用该工质，多级透平的折合转速、折合功率、膨胀比相等三个模化准则同时满足，气动参数与设计值偏差不超过−0.54%～0.52%。
- 多级透平试验 /
- 模化准则 /
- 相似性 /
- 工质物性 /
- 比热比 /
- 气动载荷
Abstract:
For the improvement of the flow field similarity in multi-stage turbine modeling tests operating at medium temperature level, a three-dimensional numerical model of a two-stage turbine was constructed and validated. The influence of the test modeling criteria selection on the flow field similarity was quantitatively studied and a new method for adjusting the specific heat ratio of working fluid was proposed. Results indicated that, the specific heat ratio of working fluid under medium temperature modeling conditions was not equal to the design value, resulting in a gradual decrease of the flow field similarity along the flow direction in the multi-stage turbine; When ensuring the similarity criterion of expansion ratio, the aerodynamic load coefficient of the last stage turbine blade was reduced by 4.78%, and the blade outlet flow angle deviated by 3°—5°; When ensuring the similarity criterion of corrected power, the corrected speed of the last turbine stage is 1.29% higher, and the back pressure for the film cooling flow of the blade decreased by 2.5%—6.5%; The test working fluid generated by combusting air into a gas and mixing with vapor had the same values of specific heat ratio to the real gas used in the different classes of heavy duty gas turbine. As this working fluid was used in the test condition at medium temperature level, the three modeling criteria including the corrected speed, the corrected power and the expansion ratio were satisfied together, and the deviation of aerodynamic parameters from the design values were within the range of −0.54% to 0.52%.
- multi-stage turbine test /
- modeling criteria /
- similarity /
- working fluid property /
- specific heat ratio /
- aerodynamic load

HTML

图 1 透平子午流道

Figure 1. Meridian flow passage of turbine

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图 2 数值计算网格与冷气分布

Figure 2. Numerical calculation grid and cooling air distribution

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图 3 透平出口温比沿叶展分布

Figure 3. Temperature ratio spanwise distribution at turbine outlet

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图 4 透平出口压比沿叶展分布

Figure 4. Pressure ratio spanwise distribution at turbine outlet

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图 5 透平流道沿程静压分布

Figure 5. Static pressures distribution along turbine flow passage

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图 6 重型燃气轮机透平Smith图

Figure 6. Smith chart for heavy duty gas turbine

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图 7 末级透平静叶出口马赫数沿叶展分布

Figure 7. Mach number spanwise distribution at vane outlet of last turbine stage

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图 8 末级透平动叶出口马赫数沿叶展分布

Figure 8. Mach number spanwise distribution at blade outlet of last turbine stage

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图 9 末级透平静叶出口膨胀比沿叶展分布

Figure 9. Expansion ratio spanwise distribution at vane outlet of last turbine stage

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图 10 末级透平动叶出口膨胀比沿叶展分布

Figure 10. Expansion ratio spanwise distribution at blade outlet of last turbine stage

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图 11 末级透平动叶出口气流角沿叶展分布

Figure 11. Flow angle spanwise distribution at blade outlet of last turbine stage

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图 12 末级透平动叶$ \Delta {p}_{\mathrm{s}} $分布

Figure 12. $ \Delta {p}_{\mathrm{s}} $ distribution at blade of last turbine stage

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图 13 工质比热比曲线

Figure 13. Specific heat ratio curves of working fluid

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图 14 工质比热比对比

Figure 14. Working fluid specific heat ratio comparison

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图 15 末级透平动叶出口气流角沿叶展分布

Figure 15. Flow angle spanwise distribution at blade outlet of last turbine stage

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图 16 末级透平动叶出口马赫数沿叶展分布

Figure 16. Mach number spanwise distribution at blade outlet of last turbine stage

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图 17 末级透平动叶出口膨胀比沿叶展分布

Figure 17. Expansion ratio spanwise distribution at blade outlet of last turbine stage

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表 1 计算边界条件

Table 1. Boundary conditions for calculation

参数	试验工况	数值计算
$ {p}_{\mathrm{t},0} $/kPa	345.97	345.97
$ {T}_{\mathrm{t},0} $/K	709.3	709.3
总-静膨胀比	5.289	5.289
转速/（r/min）	8283	8283
冷气流量/（kg/s）	2.08	2.08

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表 2 性能参数对比

Table 2. Comparison of performance parameters

参数	试验（RDG29工况）	数值计算
总-总膨胀比	4.933	4.909
动叶进口流量/（kg/s）	11.82	11.96
总-总效率/%	92.55	92.04

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表 3 算例设置与边界条件

Table 3. Calculations setting and boundary conditions

参数	算例A	算例B	算例C
比热比	1.308	1.354	1.354
进口总温/K	1588	794	794
进口总压/kPa	1303	650	650
转速/（r/min）	12630	8931	8931
总-静膨胀比	5.289	5.289	5.53

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表 4 首级透平参数对比

Table 4. Comparison of first turbine stage parameters

参数	算例A	算例B		算例C
参数	算例A	数值	与算例A的偏差/%	数值	与算例A的偏差/%
进口总温/K	1588	794		794
比热比	1.308	1.354		1.354
折合转速n₁	33.19	33.19	0	33.19	0
折合功率l	0.2089	0.2087	−0.10	0.2094	0.24
载荷系数ψ	1.586	1.585	−0.06	1.590	0.25
流量系数φ	0.4904	0.4898	−0.12	0.4909	0.10

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表 5 末级透平参数对比

Table 5. Comparison of last turbine stage parameters

参数	算例A	算例B		算例C
参数	算例A	数值	与算例A的偏差/%	数值	与算例A的偏差/%
进口总温/K	1312.9	640.39		639.9
比热比	1.318	1.371		1.371
折合转速n₁	36.50	36.96	1.25	36.97	1.29
折合功率l	0.1675	0.1635	−2.39	0.1715	2.39
载荷系数ψ	1.051	1.001	−4.78	1.049	−0.20
流量系数φ	0.5535	0.5363	−3.10	0.5541	0.12

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表 6 工质组分调整结果

Table 6. Working fluid components adjusting results

参数		数据
天然气与空气质量比		0.0236
燃烧温升/K		985
燃烧后质量占比/%	氮气*	75.09
	氧气	13.41
	水蒸气	5.18
	二氧化碳	6.32
水蒸气与燃气质量比		0.5411
掺混后质量占比/%	氮气*	48.01
	氧气	8.57
	水蒸气	39.38
	二氧化碳	4.04
注：*表示大气原有二氧化碳和氩气已折算入氮气的质量占比。

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表 7 透平参数对比

Table 7. Comparison of turbine parameters

参数		算例A	算例D	偏差/%
气体常数/（J/（kg·K））		287.05	353.38
首级透平	入口比热比	1.308	1.307	−0.08
	折合转速n₂	1.840	1.845	0.27
	折合功率l₂	0.0009160	0.0009196	0.39
	载荷系数ψ	1.586	1.591	0.32
	流量系数φ	0.4904	0.4897	−0.14
	总-静膨胀比	2.608	2.613	0.19
首级透平和末级透平入口温度之比		1.210	1.211	0.15
末级透平	入口比热比	1.318	1.320	0.15
	折合转速n₂	2.020	2.026	0.30
	折合功率l₂	0.0009283	0.0009332	0.52
	载荷系数ψ	1.051	1.049	−0.19
	流量系数φ	0.553	0.550	−0.54
	总-静膨胀比	2.195	2.190	−0.23

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