超临界二氧化碳向心透平轮背间隙内风阻损失及流动特性研究

赵卓斌; 邓清华; 陈祎一; 刘安琦; 李军

doi:10.7652/xjtuxb202607003

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超临界二氧化碳向心透平轮背间隙内风阻损失及流动特性研究

专题超临界流体前沿应用 | 更新时间：2026-07-09

- 超临界二氧化碳向心透平轮背间隙内风阻损失及流动特性研究
- Windage Loss and Flow Characteristics in Impeller Back Gaps of sCO₂ Radial Inflow Turbines
- 西安交通大学学报 2026年60卷第7期页码：24-34
- 作者机构：
  
  西安交通大学能源与动力工程学院，710049，西安
- 作者简介：
  
  作者简介：赵卓斌（1998—），男，博士生；
  邓清华（通信作者），男，副教授，博士生导师。
- 基金信息：
  
  国家重点研发计划资助项目(2023YFB4102203);国家自然科学基金联合基金重点资助项目(U20A20303)
- DOI：10.7652/xjtuxb202607003
  中图分类号： TK14
- 收稿：2025-09-10，
  
  纸质出版：2026-07-10
- 稿件说明：
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赵卓斌, 邓清华, 陈祎一, 等. 超临界二氧化碳向心透平轮背间隙内风阻损失及流动特性研究[J]. 西安交通大学学报, 2026,60(7):24-34.

ZHAO Zhuobin, DENG Qinghua, CHEN Yiyi, et al. Windage Loss and Flow Characteristics in Impeller Back Gaps of sCO₂ Radial Inflow Turbines[J]. Journal of Xi'an Jiaotong University, 2026, 60(7): 24-34. DOI: 10.7652/xjtuxb202607003.
赵卓斌, 邓清华, 陈祎一, 等. 超临界二氧化碳向心透平轮背间隙内风阻损失及流动特性研究[J]. 西安交通大学学报, 2026,60(7):24-34. DOI： 10.7652/xjtuxb202607003.

ZHAO Zhuobin, DENG Qinghua, CHEN Yiyi, et al. Windage Loss and Flow Characteristics in Impeller Back Gaps of sCO₂ Radial Inflow Turbines[J]. Journal of Xi'an Jiaotong University, 2026, 60(7): 24-34. DOI: 10.7652/xjtuxb202607003. DOI：

摘要

针对当前带有减重结构的复杂轮背间隙内风阻损失机理认识不足的现状，采用数值方法研究了旋转雷诺数、通流雷诺数、相对间隙等关键参数对风阻损失的影响规律并揭示了间隙内的流动机理。基于微分切应力理论构建了斜面形状间隙的层流理论模型，并提出了将复杂轮背间隙等效为双相对间隙耦合形式的简化轮背间隙风阻损失模型。结果表明：轮背间隙内的风阻损失随旋转雷诺数和通流雷诺数的增大而增大，随相对间隙增大而减小，在这种叠加流态下核心区形成补偿性径向内流，使径向速度呈现出两种方向；当旋转雷诺数为1×10

时，相较于标准盘类轮背间隙，带减重结构的轮背间隙风阻损失降低了7.27%；带减重结构轮背间隙内的流动可划分为4个特征区域，其中转子泵送区源于周向与径向流动的叠加作用，通流雷诺数的增大会抑制泵送效应，从而影响核心区流体的速度分布并加剧风阻损失；复杂轮背间隙风阻损失模型与数值结果的相对偏差在15%以下。研究结果可为超临界二氧化碳向心透平气动优化设计提供理论支撑与工程指导。

Abstract

To address the limited understanding of windage loss mechanisms in complex back gaps featuring weight reduction structures，numerical simulations are conducted to investigate the effects of key parameters such as rotational Reynolds number，throughflow Reynolds number and relative gaps on windage losses and to elucidate the flow mechanisms within the gaps.A laminar theoretical model for slope wall gaps is developed based on differential shear stress theory，and a simplified windage loss model for impeller back gaps is proposed by representing the complex back gap as an equivalent coupling of two relative gaps.Results demonstrate that windage losses in impeller back gaps increase with rising rotational and throughflow Reynolds numbers but decrease with increasing relative gaps.In this superimposed flow regime，a compensatory radial inflow is formed in the core region，causing radial velocities to exhibit two directions.At a rotational Reynolds number of 1×10

，the windage loss in the impeller back gap featuring weight reduction structure is reduced by 7.27% compared to that in a standard disk-type impeller back gap.The flow within the gap is classified into 4 characteristic regions；the rotor pumping region is induced by the superposition of circumferential and radial flows，and an increase in throughf

low Reynolds number suppresses the pumping effect，thereby altering the velocity distribution of fluid in the core region and exacerbating windage losses.The proposed windage loss model for complex impeller back gaps predicts windage losses with a relative deviation of less than 15% compared with numerical results. These findings provide both theoretical validation and engineering guidance for aerodynamic optimization design of supercritical carbon dioxide（sCO

）radial inflow turbines.

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