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叶片开槽结构对超临界二氧化碳离心压缩机特性的影响数值模拟

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叶片开槽结构对超临界二氧化碳离心压缩机特性的影响数值模拟

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Study on Effect of Blade Groove Structure on Characteristics of Supercritical Carbon Dioxide Centrifugal Compressor

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doi: 10.19666/j.rlfd.202609006

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【目的】针对超临界二氧化碳（sCO₂）离心压缩机运行过程中工质凝结导致性能下降问题。提出一种吸力面前缘开槽叶片结构与进口温度协同调控方法。

【方法】以带吸力面前缘开槽结构的sCO₂离心压缩机为研究对象，采用数值模拟方法，研究不同工况下压缩机内部流动特性、凝结行为及性能演化规律。

【结果】结果表明，叶片开槽结构能够有效减少叶轮内部凝结区域，但开槽结构引起的局部流动扰动使最大等熵效率由普通叶片的84.60%降低至83.20%。随着进口温度升高，工质凝结得到有效抑制，同时开槽结构造成的气动损失逐渐恢复；当温度由310 K升高至315 K时，等熵效率由82.1%提升至83.5%，无量纲凝结体积显著降低，并在314 K后降低至0.211。当进口温度超过315 K后，凝结抑制效果提升有限，但由于工质密度降低导致压比下降，等熵效率逐渐降低。

【结论】综合考虑工质的凝结、气动性能及压比变化规律，315 K为本文研究开槽结构sCO₂离心压缩机最佳运行温度。研究提出的叶片结构与运行参数协同优化策略，可为sCO₂离心压缩机高效运行及工质凝结抑制设计提供理论依据。

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[Objective] The supercritical carbon dioxide (sCO₂) Brayton cycle has become a promising power‑generation technology owing to its high cycle efficiency and compact component layout. Nevertheless, condensation phase‑change near the critical point inside centrifugal compressors severely threatens operational reliability. Severe working fluid condensation will not only lead to mass flow degradation and shrinkage of the stable operating envelope, but liquid droplet impingement upon high speed spinning blades may also trigger hidden risks concerning blade structural integrity and mechanical strength. The suction‑side leading‑edge grooving modification can mitigate local condensation, yet it introduces extra flow perturbation and aerodynamic performance degradation. It remains insufficiently understood how to coordinate the condensation‑suppression benefit and efficiency penalty brought by grooved blades. This work aims to explore the collaborative optimization between the grooved‑blade structure and inlet‑temperature adjustment for sCO₂ centrifugal compressors.

[Methods] Numerical simulation based on computational fluid dynamics was carried out for the sCO₂ centrifugal compressor with suction‑side leading‑edge grooving. The homogeneous binary mixture model was adopted to capture two‑phase condensation behavior, while the k‑ω SST turbulence model was employed to resolve complex boundary‑layer flow and local separation. After grid‑independence examination and model validation against Sandia National Laboratory’s experimental data, the internal flow field, condensation characteristics, and overall aerodynamic performance were systematically investigated under inlet temperatures ranging from 310 K to 319 K at the fixed mass‑flow rate of 61 kg/s, which corresponds to the peak‑efficiency working point of the prototype compressor.

[Results] The grooved‑blade configuration effectively elevates static pressure and static temperature within the core condensation zone close to the blade leading‑edge, drastically cutting the dimensionless condensation volume. However, local vortices and flow disturbance induced by the groove reduce the maximum isentropic efficiency from 84.60 % of the baseline smooth blade down to 83.20 %. Raising the inlet temperature properly compensates for such performance loss. Within 310 K‑315 K, compressor isentropic efficiency climbs continuously from 82.1 % to 83.5 %. As inlet temperature increases from 310 K to 314 K, the dimensionless condensation volume drops sharply and approaches nearly zero beyond 314 K, proving that reasonable inlet‑temperature elevation eliminates most impeller internal condensation regions. When inlet temperature exceeds 315 K, the condensation‑suppression capability barely improves further. Even so, reduced working‑fluid density impairs the pressure‑boosting capacity, leading to continuous decline of total pressure ratio and gradual deterioration of isentropic efficiency.

[Conclusions] Balancing condensation‑control effectiveness, isentropic efficiency, and pressure‑ratio characteristics comprehensively, 315 K is identified as the optimal inlet operating temperature for this grooved‑blade sCO₂ centrifugal compressor. At this condition, the condensation risk is well restrained, and the aerodynamic penalty originating from blade grooving is largely recovered. The present findings provide practical references for blade‑structure optimization and operating‑parameter matching of sCO₂ centrifugal compressors in Brayton‑cycle power systems.

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. 叶片开槽结构对超临界二氧化碳离心压缩机特性的影响数值模拟. 热力发电, : - . DOI: 10.19666/j.rlfd.202609006

. Study on Effect of Blade Groove Structure on Characteristics of Supercritical Carbon Dioxide Centrifugal Compressor[J]. Thermal Power Generation, : - . DOI: 10.19666/j.rlfd.202609006

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doi: 10.19666/j.rlfd.202609006

首发时间：2026-11-04

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2种不同金属材料的力学参数

科 Family	属数 Number of genus	种数 Number of species	占总种数比例 Percentage of total species (%)	属 Genus	种数 Number of species	占总种数比例 Percentage of total species (%)
鹅膏菌科Amanitaceae	2	11	5.26	鹅膏菌属 Amanita	10	4.78
小菇科 Mycenaceae	2	12	5.74	丝盖伞属 Inocybe	5	2.39
多孔菌科 Polyporaceae	8	14	6.70	蜡蘑属 Laccaria	5	2.39
红菇科 Russulaceae	3	23	11.00	小皮伞属 Marasmius	6	2.87
				小菇属 Mycena	11	5.26
				光柄菇属 Pluteus	5	2.39
				红菇属 Russula	17	8.13
				栓菌属 Trametes	5	2.39

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