Numerical investigation and verification on the inlet and exhaust housings of a supercritical carbon dioxide axial turbine

LIU Hongdan; WANG Lei; ZHOU Dong; DAN Guangju; LI Hongzhi; HE Dan; DENG Dejian

doi:10.19666/j.rlfd.202208231

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Numerical investigation and verification on the inlet and exhaust housings of a supercritical carbon dioxide axial turbine

更新时间：2025-09-28

- Numerical investigation and verification on the inlet and exhaust housings of a supercritical carbon dioxide axial turbine
- Thermal Power Generation Vol. 52, Issue 6, Pages: 135-145(2023)
- 作者机构：
  
  1. 重庆江增船舶重工有限公司
  2. 船舶与海洋工程特种装备和动力系统国家工程研究中心
  3. 船用涡轮增压器研发重庆市工业和信息化重点实验室
  4. 西安热工研究院有限公司
- 作者简介：
- 基金信息：
- DOI：10.19666/j.rlfd.202208231
  CLC： TM61
- Published：2023
- 稿件说明：
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LIU Hongdan, WANG Lei, ZHOU Dong, et al. Numerical investigation and verification on the inlet and exhaust housings of a supercritical carbon dioxide axial turbine[J]. Thermal power generation, 2023, 52(6): 135-145.
DOI：

LIU Hongdan, WANG Lei, ZHOU Dong, et al. Numerical investigation and verification on the inlet and exhaust housings of a supercritical carbon dioxide axial turbine[J]. Thermal power generation, 2023, 52(6): 135-145. DOI： 10.19666/j.rlfd.202208231.

摘要

透平作为超临界二氧化碳（S-CO_2）布雷顿循环发电系统的核心设备之一，目前缺乏针对机组整体性能的可靠评估与试验验证。针对某S-CO_2机组轴流透平不同工况试验测试结果进行了仿真与测试的对比分析，重点讨论了进排气壳体对机组性能的影响。研究结果表明：采用的数值计算方法和综合考虑进排气壳体的计算模型能够较为准确地评估透平不同负荷工况性能；与测试结果相比，效率误差最大为1.77百分点，流量误差最大为5.6%。该透平动叶采取叶冠型式可降低泄漏掺混损失，与普通叶顶间隙型式相比，机组效率提升1.4百分点。有无进排气壳体的仿真结果显示，透平机组（涡轮级+进排气壳体）效率与涡轮级效率相比，最大降低了2.9百分点，主要是由进排气壳体内部的流动损失造成。研究成果为后续S-CO_2轴流透平设计与性能研究提供了技术支撑和依据。

Abstract

As the core equipment of supercritical carbon dioxide(S-CO_2) Brayton cycle

there is a lack of reliable evaluation and test verification of the overall performance. An in-depth simulation and performance analysis of one axial turbine are carried out

focusing on the impact of inlet and exhaust housings with experiment results for different operating conditions. The results show that the numerical calculation method and model are able to evaluate the performance at different load conditions more accurately. Compared with the test results

the maximum efficiency error is 1.77 percentage point and the flow rate error remains within 5.6%. The crown pattern can reduce leakage and mixing losses

and increase efficiency by 1.4 percentage point compared to the common top clearance pattern. Simulation results show that the efficiency of turbine unit is reduced compared to turbine stage

with a maximum reduction by 2.9 percentage point. The flow loss of inlet and exhaust housings is the main reason for the reduction. The research results can provide technical support for the design and performance simulation of S-CO_2 axial turbines.

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