A New Approach to Suppress Tip Leakage Flow Utilizing Induced Shock Wave in Tip Region of a Transonic Compressor Rotor

CUI Weiwei, YAO Fei, LI Zongming, WANG Xiaonan, CHANG Guozhang, WANG Cuiping

热科学学报 ›› 2024, Vol. 33 ›› Issue (6) : 2059-2074.

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Journal of Thermal Science

热科学学报
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热科学学报 ›› 2024, Vol. 33 ›› Issue (6) : 2059-2074. DOI: 10.1007/s11630-024-2052-7  CSTR: 32141.14.JTS-024-2052-7

A New Approach to Suppress Tip Leakage Flow Utilizing Induced Shock Wave in Tip Region of a Transonic Compressor Rotor

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A New Approach to Suppress Tip Leakage Flow Utilizing Induced Shock Wave in Tip Region of a Transonic Compressor Rotor

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摘要

间隙泄漏流对高负荷压气机的流动稳定性具有显著影响。因此，本文提出了一种新方法，利用转子叶顶吸力面侧诱导激波来抑制跨音转子间隙泄漏流强度及其影响范围。通过设计三种具有不同周向扩张度的渐扩型间隙结构方案，以揭示该新方法的作用机理。在叶顶周向渐扩型间隙结构（由转子叶顶压力面侧指向吸力面侧）的作用下，新方案使得跨音转子的叶顶间隙区的超音速泄漏流射流形成明显加速现象。在加速膨胀后的超音速泄漏流与叶尖区域高压主流流体之间压差的作用下，新转子方案的叶尖间隙区域就会产生诱导激波。借助于该诱导激波，可以大幅减小泄漏流由转子叶顶吸力面侧流出时的速度和流量。此外，诱导激波对转子叶顶超音速泄漏流射流的抑制效果与其强度和周向位置密切相关。相比于具有均匀设计间隙的原型方案，当转子叶顶间隙的周向扩张角等于8°时，诱导激波对间隙泄漏流的抑制效果相对最优，能够实现跨音转子失速裕度增加5%以上，且引起的等熵效率下降不超过0.4%。

Abstract

Tip leakage flow affects the flow stability of high-loading compressors significantly. Therefore, a novel approach via induced shock wave near suction-side edge of blade tip was proposed to suppress the strength and influence range of leakage flow in a transonic rotor. Three new schemes with different circumferentially diverging degrees of clearance were designed to reveal the mechanism of the new approach. Through the action of the circumferentially diverging clearance (from the pressure side to the suction side over blade tip), a much more dramatic acceleration of the supersonic leakage jet flow appeared over blade tip of the new schemes. An induced shock wave was produced near the suction side edge of blade tip due to the pressure difference between the discharging leakage flow and the surrounding high-pressure mainflow in tip channel. As a result, both the mass flow rate and the outlet velocity of leakage flow were reduced significantly via the induced shock wave. Meanwhile, the suppressing effect of the new approach on the tip leakage jet flow was closely related to the strength and circumferential location of the induced shock wave. With the aids of the induced shock wave, the largest improvement of tip flow characteristics with an over 5% increase in stall margin was realized in new transonic rotor when the circumferential divergence angle equals 8°, accompanied with no more than a 0.4% decrease in isentropic efficiency.

关键词

circumferentially diverging clearance / induced shock wave / leakage flow / low-velocity region / stall margin enhancement

Key words

circumferentially diverging clearance / induced shock wave / leakage flow / low-velocity region / stall margin enhancement

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CUI Weiwei , YAO Fei , LI Zongming , WANG Xiaonan , CHANG Guozhang , WANG Cuiping. A New Approach to Suppress Tip Leakage Flow Utilizing Induced Shock Wave in Tip Region of a Transonic Compressor Rotor[J]. 热科学学报, 2024, 33(6): 2059-2074 https://doi.org/10.1007/s11630-024-2052-7
CUI Weiwei , YAO Fei , LI Zongming , WANG Xiaonan , CHANG Guozhang , WANG Cuiping. A New Approach to Suppress Tip Leakage Flow Utilizing Induced Shock Wave in Tip Region of a Transonic Compressor Rotor[J]. Journal of Thermal Science, 2024, 33(6): 2059-2074 https://doi.org/10.1007/s11630-024-2052-7

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基金

This research work was sponsored by the General Program of National Natural Science Foundation of China (Grant No. 52076124) and the National Science and Technology Major Project (Grant No. J2019-II-0014-0035).

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Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2024
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