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叶尖小翼周向最宽位置对高负荷压气机级特性影响的研究

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推进技术 2024年第4期45卷 70-81页

作者：赵傲胡义吴宛洋钟兢军上海海事大学商船学院上海201306

针对叶尖小翼扩稳技术,采用数值方法在改变叶尖小翼宽度的基础上,考虑了叶尖小翼几何形状的周向最宽位置对高负荷压气机级性能的影响。研究结果表明,叶尖小翼宽度越大且最宽位置靠近叶片两端时,压气机级的稳定工作裕度的提升越明显。叶... 详细信息

针对叶尖小翼扩稳技术,采用数值方法在改变叶尖小翼宽度的基础上,考虑了叶尖小翼几何形状的周向最宽位置对高负荷压气机级性能的影响。研究结果表明,叶尖小翼宽度越大且最宽位置靠近叶片两端时,压气机级的稳定工作裕度的提升越明显。叶尖小翼宽度为2.0倍叶顶宽度时,且周向最宽位置位于转子前缘25%轴向弦长时,叶尖小翼最多使叶顶泄漏流的质量流量减少了7.66%,提升了压气机级通道内流体的轴向速度,抑制了转子及静子叶片叶表的分离情况,从而延缓了压气机级的失速,压气机级的稳定工作裕度提升了29.18%。

关键词：高负荷压气机叶尖小翼级特性稳定工作裕度数值研究

叶尖小翼对跨声速压气机级稳定工作裕度的影响

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航空动力学报 2024年第1期39卷 110-121页

作者：钟兢军赵傲胡义吴宛洋上海海事大学商船学院上海201306

为了揭示叶尖小翼对跨声速压气机级气动性能的影响机制,利用数值方法研究了压气机级转子叶片上加装不同宽度压力面/吸力面叶尖小翼的作用效果和扩稳机制。同时,提出一种更加系统的叶尖小翼结构设计方法以优化叶尖小翼技术在压气机上的应... 详细信息

为了揭示叶尖小翼对跨声速压气机级气动性能的影响机制,利用数值方法研究了压气机级转子叶片上加装不同宽度压力面/吸力面叶尖小翼的作用效果和扩稳机制。同时,提出一种更加系统的叶尖小翼结构设计方法以优化叶尖小翼技术在压气机上的应用,使压气机级压比和绝热效率基本保持不变的前提下提升其稳定工作裕度。研究结果表明:随着压力面小翼宽度的增加,压气机级的稳定工作裕度分别增加了6.01%、9.90%、10.76%、11.43%,压力面叶尖小翼改变了转子叶顶气流偏转角,抑制了叶顶泄漏流的产生和泄漏涡破碎,提升了压气机级的流通能力,同时减弱了静子叶片吸力侧的分离损失。

关键词：叶尖小翼跨声速压气机级叶顶泄漏稳定工作裕度扩稳机制

设计马赫数下高负荷压气机叶栅流动损失的参数化调控

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推进技术 2024年第10期45卷 41-55页

作者：阚晓旭雷浩东吴宛洋钟兢军上海海事大学商船学院上海201306

为有效预测、调控高负荷压气机平面叶栅的旋涡结构与流动损失,本文以某高负荷的可控扩散叶型(CDA)拉伸生成的平面叶栅为研究对象,采用数值计算方法、损失权重系数分析方法研究了在几何、气动变量条件下,叶栅流道内的旋涡结构与流动损失... 详细信息

为有效预测、调控高负荷压气机平面叶栅的旋涡结构与流动损失,本文以某高负荷的可控扩散叶型(CDA)拉伸生成的平面叶栅为研究对象,采用数值计算方法、损失权重系数分析方法研究了在几何、气动变量条件下,叶栅流道内的旋涡结构与流动损失之间的关联性。揭示了稠度,安装角和进、出口几何角等参数变化影响旋涡结构损失与出口截面损失的作用机理,建立了相对完整的各几何参数影响流动损失及损失权重系数的参数化表达式。结果表明:根据参数化表达式来对不同参数下的最优解进行预测后,各单参数变量下对应的最佳优化结果平均绝对误差不超过3%,对于影响损失较大的几何参数的损失权重系数预测时,平均绝对误差不超过6%。通过本文所提出的参数化方法,与传统损失模型相比,在计算高负荷压气机叶栅流动损失方面的精度得到了显著提升,一些预测精度提升了一个数量级。本文以最佳参数预测、重构一套优化叶栅,实际数值计算结果表明,相较于原型叶栅,优化叶栅出口截面损失下降了11.18%,扩压能力提升了8.04%,达到了定性预测的目的。

关键词：压气机平面叶栅旋涡结构流动损失参数化方法优化重构

Variable Clearance Characteristics of High Subsonic Compressor Cascades with Blade Tip Winglets

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Journal of Thermal Science 2022年第2期31卷 495-510页

作者： WU Wanyang zhong jingjun Merchant Marine College Shanghai Maritime UniversityShanghai 201306China

The gas turbine is the main power equipment for naval ship and special civil ship,while the compressor is one of the core structures of the gas *** existing tip clearance could prevent the compressor blade and casing ***,the flow loss in the tip region caused by the tip clearance will degrade the performance of the *** improve the variable clearance characteristics of the high subsonic compressor cascades,the cascades with tip clearances of 1%,2%and 3%chord length are studied through experimental measurements and numerical *** research results prove that the pressure surface tip winglet can cause a significant improvement effect under most working *** the blade tip clearance size is gradually increasing within a reasonable range,the improvement effect becomes more remarkable,and the optimal tip winglet case *** tip clearance is 1%chord length,the PTW1.0 case(the width of the pressure surface tip winglet is 1.0 time of the original tip)reduces the flow loss by 3.09%compared with the NTW case(No Tip Winglet).When tip clearance is 2%chord length,the flow loss of PTW1.5 case(the width of the pressure surface tip winglet is 1.5 times of the original tip)is reduced by 3.46%.When tip clearance is 3%chord length,all alternative tip winglets reduce the total pressure loss,and PTW2.0 case(the width of the pressure surface tip winglet is 2.0 times of the original tip)is the best choice,which has a 6.53%degree of improvement.

关键词： high subsonic compressor blade tip winglet tip clearance pressure surface experimental measurement

Effect of blade tip winglet on the performance of a highly loaded transonic compressor rotor

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Chinese Journal of Aeronautics 2016年第3期29卷 653-661页

作者： Han Shaobing zhong jingjun Marine Engineering College Dalian Maritime University

The tip leakage flow has an important influence on the performance of transonic com- pressor. Blade tip winglet has been proved to be an effective method to control the tip leakage flow in compressor, while the physical mechanisms of blade tip winglet have been poorly understood. A numerical study for a highly loaded transonic compressor rotor has been conducted to understand the effect of varying the location of blade tip wing]et on the performance of the rotor. Two kinds of tip winglet were designed and investigated. The effects of blade tip winglet on the compressor over- all performance, stability and tip flow structure were presented and discussed, It is found that the interaction of the tip winglet with the flow in the tip region is different when the winglet is located at suction-side or pressure-side of the blade tip. Results indicate that the suction-side winglet （SW） is ineffective to improve the performance of compressor rotor. In addition, a significant stall range extension equivalent to 33.74% with a very small penalty in efficiency can be obtained by the pressure-side winglet （PW）. An attempt has been made to explain the fundamental mechanisms of blade tip winglet in detail.

关键词： Blade tip winglet Numerical study Shock wave/tip leakage vor-tex interaction Stall range Tra,asonic compressor rotor

Research Progress of Tip Winglet Technology in Compressor

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Journal of Thermal Science 2021年第1期30卷 18-31页

作者： zhong jingjun WU Wanyang HAN Shaobing Merchant Marine College Shanghai Maritime UniversityShanghai 201306China Naval Architecture and Ocean Engineering College Dalian Maritime UniversityDalian 116026China

In the present study,the research progress of tip winglets that control tip clearance leakage flow in compressors is ***,the effects of tip leakage flow on the aerodynamic performance of the compressor are ***,the development of tip winglet technology is ***,a series of studies on compressor tip winglet technology are ***,the effects of tip winglets on the aerodynamic performance of rectangular cascades of low-speed and high-subsonic compressors,subsonic compressor rotor and transonic compressor rotor are discussed,respectively,and the control effect of tip winglet technology combined with tip groove design on tip leakage is ***,the subsequent development direction and research prospect of compressor tip winglet technology are presented.

关键词： blade tip winglet compressor tip leakage flow tip leakage vortex

Numerical Simulation and Experimental Study of the Submarine's Cold Wake Temperature Character

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Journal of Thermal Science 2014年第3期23卷 253-258页

作者： CHEN Shengtao zhong jingjun SUN Peng Marine Engineering College Dalian Maritime University

The temperature difference of the submarine's wake on the sea surface is the base for the IR detection. In this paper, the temperature difference on the sea surface caused by the submarine's propellers and the submarine's hull is studied by solving the three dimensional N-S equations. The results show that under the condition of sea temperature surroundings of minus gradient, such as in summer the upper water's temperature is higher than the lower water, it is cold wake on the sea surface and hot wake on the submarine's plane. The temperature difference between the wake and the water around in the wake's initial part becomes more and more obvious as the wake's distance gets longer. Through the IR camera, the submarine's propeller wake is studied under the same temperature status. Obvious IR temperature difference signals can be observed and it is consistent with the numerical simulation for the submarine.

关键词： submarine wake temperature difference IR

Reconstruction Method for Running Shape of Rotor Blade Considering Nonlinear Stiffness and Loads

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Journal of Thermal Science 2017年第5期26卷 431-439页

作者： WANG Yongliang KANG Da zhong jingjun Marine Engineering College Dalian Maritime University Dalian 116026 China

The aerodynamic and centrifugal loads acting on the rotating blade make the blade configuration deformed comparing to its shape at rest. Accurate prediction of the running blade configuration plays a significant role in examining and analyzing turbomachinery performance. Considering nonlinear stiffness and loads, a reconstruction method is presented to address transformation of a rotating blade from cold to hot state. When calculating blade deformations, the blade stiffness and load conditions are updated simultaneously as blade shape varies. The reconstruction procedure is iterated till a converged hot blade shape is obtained. This method has been employed to determine the operating blade shapes of a test rotor blade and the Stage 37 rotor blade. The calculated results are compared with the experiments. The results show that the proposed method used for blade operating shape prediction is effective. The studies also show that this method can improve precision of finite element analysis and aerodynamic performance analysis.

关键词： Blade reconstruction Fluid-structure interaction Aeroelasticity Nonlinearity

Research on Calculation Method of Aerodynamic Parameters of Supersonic Probe Based on Gas Compressibility Factor

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Journal of Thermal Science 2022年第1期31卷 111-119页

作者： zhong jingjun HUANG Gangfeng WU Wanyang KAN Xiaoxu Merchant Marine College Shanghai Maritime University1550 Haigang AvenuePudong DistrictShanghai 201306

The supersonic multi-hole probe is an essential test tool for wind tunnel experiments, which is necessary to develop the basic research of improving the measurement accuracy and expanding the application of the probes.

关键词： supersonic flow probe gas compressible factor aerodynamic parameter error analyses