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Impacts of Multi-Swirl Interaction Pattern on Self-Excited Instability Combustion Characteristics

Journal of Thermal Science 2025年第02期 672-688页

作者： JIN Ming LIU Zhannan LU Yudi GE Bing zang shusheng School of Mechanical Engineering Shanghai Jiao Tong University

Experimental and numerical investigations have been carried out on the effects of multi-swirl interaction patterns on self-excited unstable combustion characteristics based on a five-nozzle can *** multi-swirl interaction patterns include equal swirl intensity interaction and strong-weak swirl *** thermo-acoustic instability characteristics indicate that increasing the central nozzle swirl intensity transforms the interaction pattern from equal swirl intensity interaction to strong-weak swirl interaction,which can significantly weaken the thermo-acoustic coupling effect under low equivalence ratio conditions,and substantially reduce the dynamic pressure amplitude during unstable *** instantaneous flame structures show that the multi-swirl flames exhibit chaotic oscillations under low equivalence ratio *** equivalence ratios greater than 0.71,a clear flame interaction boundary appears,and the flames can exhibit periodic oscillations in a regular ***,different interaction patterns result in the completely different phase oscillations in the central and outer *** time-averaged flame structures also indicate that strong-weak swirl interaction leads to an increase in the flame angle and a decrease in the flame length for both the central and outer flames,and the variations in the flame angle and length have great impacts on the thermo-acoustic instability *** fuel-staging combustion characteristics demonstrate that the instability combustion conditions with a dominant frequency of 100 Hz are greatly broadened by the strong-weak swirl interaction pattern,and the overlapping operating conditions between this mode and other modes are greatly *** implies that it is more flexible to adjust the thermo-acoustic unstable mode,which is conducive to the passive suppression of thermo-acoustic instability.

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Numerical Investigation of Active Tip-clearance Control through Tip Cooling Injection in an Axial Turbine Cascade

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Journal of Thermal Science 2009年第4期18卷 306-312页

作者： Maosheng Niu shusheng zang Institute of Turbomachinery School of Mechanical EngineeringShanghai JiaoTong UniversityShanghai 200240China Professor

This paper presents a numerical investigation of an active tip-clearance control method based on cooling injectionfrom the blade tip surface. It aims to study the influences of air injection on controlling tip clearance flow, withemphasis on the effects of the injection location on secondary flow and the potential thermal benefits from thecooling jet. The results show that injection location plays an important role in the redistribution of secondary flowwithin the cascade passage. Injection located much closer to the pressure-side comer performs better in reducingtip clearance massflow and its associated losses. However, it also intensifies tip passage vortex, due to less restraintderiving from the reduced tip clearance vortex. Lower plenum total pressure is required to inject equivalentamount of cooling air, but the heat transfer condition on the blade tip surface is a bit worse than that with injectionfrom the reattachment region. Thus the optimum location of air injection should be at the tip separation vortex region.

关键词： active tip-clearance control tip cooling injection injection location tip clearance vortex passagevortex secondary flow

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Conjugate Heat Transfer Investigation on the Cooling Performance of Air Cooled Turbine Blade with Thermal Barrier Coating

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Journal of Thermal Science 2016年第4期25卷 325-335页

作者： JI Yongbin MA Chao GE Bing zang shusheng School of Mechanical and Power Engineering Shanghai Jiaotong University

A hot wind tunnel of annular cascade test rig is established for measuring temperature distribution on a real gas turbine blade surface with infrared ***,conjugate heat transfer numerical simulation is performed to obtain cooling efficiency distribution on both blade substrate surface and coating surface for *** effect of thermal barrier coating on the overall cooling performance for blades is compared under varied mass flow rate of coolant,and spatial difference is also *** indicate that the cooling efficiency in the leading edge and trailing edge areas of the blade is the *** cooling performance is not only influenced by the internal cooling structures layout inside the blade but also by the flow condition of the mainstream in the external cascade *** barrier effects of the coating vary at different regions of the blade surface,where higher internal cooling performance exists,more effective the thermal barrier will be,which means the thermal protection effect of coatings is remarkable in these *** the designed mass flow ratio condition,the cooling efficiency on the pressure side varies by 0.13 for the coating surface and substrate surface,while this value is 0.09 on the suction side.

关键词： gas turbine blade thermal barrier coating cooling efficiency conjugate heat transfer

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An Experimental Investigation of Heat Transfer Characteristics for Steam Cooling in a Rectangular Channel with Parallel Ribs

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Journal of Thermal Science 2014年第5期23卷 454-464页

作者： MA Chao CHEN Xiaoling WANG Jianfei zang shusheng JI Yongbin School of Mechanical and Power Engineering Shanghai Jiaotong University

An experimental study of heat transfer characteristics in superheated steam cooled rectangular channels with parallel ribs was *** distribution of the heat transfer coefficient on the rib-roughed channel was measured by IR *** blockage ratio(e/Dh) of the tested channel is 0.078 and the aspect ratio(W/H) is fixed *** of the rib pitch-to-height ratio(P/e) and the rib angle on heat transfer for steam cooling were *** this paper,the Reynolds number(Re) for steam ranges from 3070 to 14800,the rib pitch-to-height ratios were 8,10 and 12,and rib angles were 90°,75°,60°,and 45°.Based on results above,we have concluded that:In case of channels with 90° tranverse ribs,for larger rib pitch models(the rib pitch-to-height ratio=10 and12),areas with low heat transfer coefficient in front of rib is larger and its minimum is lower,while the position of the region with high heat transfer coefficient nearly remains the same,but its maximun of heat transfer coefficient becomes *** case of channels with inclined ribs,heat transfer coefficients on the surface decrease along the direction of each rib and show an apparent nonuniformity,consequently the regions with low Nusselt number values closely following each rib expand along the aforementioned direction and that of relative high Nusselt number values vary *** a square channel with 90° ribs at Re= 14800,wider spacing rib configurations(the rib pitch-to-height ratio=10 and 12) give an area-averaged heat transfer on the rib-roughened surface about8.4%and 11.4%more than P/e=8 model,respectively;for inclined parallel ribs with different rib angles at Re=14800,the area-averaged heat transfer coefficients of 75°,60° and 45° ribbed surfaces increase by 20.1%,42.0%and 44.4%in comparison with 90° rib angle model.45° angle rib-roughened channel leads to a maximal augmentation of the area-averaged heat transfer coefficient in all research objects in this paper.

关键词： Gas turbine cooling Steam cooling Rib-roughed channel Local heat transfer enhancement

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Comparative Study of Convective Heat Transfer Performance of Steam and Air Flow in Rib Roughened Channels

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Journal of Thermal Science 2018年第2期27卷 184-194页

作者： MA Chao JI Yongbin GE Bing zang shusheng CHEN Hua Marine engineering college Dalian Maritime University School of Mechanical Engineering Shanghai Jiao Tong University

A comparative experimental study of heat transfer characteristics of steam and air flow in rectangular channels roughened with parallel ribs was conducted by using an infrared camera. Effects of Reynolds numbers and rib angles on the steam and air convective heat transfer have been obtained and compared with each other for the Reynolds number from about 4,000 to 15,000. For all the ribbed channels the rib pitch to height ratio(p/e) is 10, and the rib height to the channel hydraulic diameter ratio is 0.078, while the rib angles are varied from 90° to 45°.Based on experimental results, it can be found that, even though the heat transfer distributions of steam and air flow in the ribbed channels are similar to each other, the steam flow can obtain higher convective heat transfer enhancement capability, and the heat transfer enhancement of both the steam and air becomes greater with the rib angle deceasing from 90° to 45°. At Reynolds number of about 12,000, the area-averaged Nusselt numbers of the steam flow is about 13.9%, 14.2%, 19.9% and 23.9% higher than those of the air flow for the rib angles of 90°,75°, 60° and 45° respectively. With the experimental results the correlations for Nusselt number in terms of Reynolds number and rib angle for the steam and air flow in the ribbed channels were developed respectively.

关键词： steam cooling air cooling rib-roughened channel gas turbine heat transfer

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几何损伤导致涡轮静叶气动衰减的CNN预测

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工程热物理学报 2022年第12期43卷 3219-3224页

作者：何庆富迟重然臧述升上海交通大学机械与动力工程学院上海200240

燃气轮机运维工作中,需根据涡轮变形损伤情况制定合理的维修策略,以更低的成本恢复燃机性能。对此,本文基于卷积神经网络(CNN),发展了一种根据几何损伤情况快速预测叶栅气动性能影响的方法。研究中,将涡轮叶片损伤分布用二维矩阵描述,... 详细信息

燃气轮机运维工作中,需根据涡轮变形损伤情况制定合理的维修策略,以更低的成本恢复燃机性能。对此,本文基于卷积神经网络(CNN),发展了一种根据几何损伤情况快速预测叶栅气动性能影响的方法。研究中,将涡轮叶片损伤分布用二维矩阵描述,生成了样本数为670的损伤叶片数据集,通过CFD仿真得到了气动性能样本。训练了CNN损伤叶片性能预测模型,并对模型进行了敏感性分析,归纳了损伤尺寸和位置对性能的影响,表明吸力面的损伤对性能的影响最显著;讨论了训练样本数对CNN精度的影响,对未来基于CNN的几何-气动关联模型构建给出了建议。

关键词：涡轮叶片损伤性能退化卷积神经网络深度学习

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不同淬熄结构下RQL燃烧室流场特性的数值研究

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航空动力学报 2019年第8期34卷 1688-1698页

作者：张亮吉雍彬葛冰臧述升上海交通大学机械与动力工程学院叶轮机械研究所

采用雷诺平均Navier-Stokes(RANS)方法对不同淬熄结构的富油/淬熄/贫油(RQL)燃烧室内定常掺混流动过程进行了数值模拟,分析了不同截面的流场结构,研究了动量通量比及淬熄孔排布方式的影响。结果表明:射流进入RQL燃烧室后发生偏转且偏转... 详细信息

采用雷诺平均Navier-Stokes(RANS)方法对不同淬熄结构的富油/淬熄/贫油(RQL)燃烧室内定常掺混流动过程进行了数值模拟,分析了不同截面的流场结构,研究了动量通量比及淬熄孔排布方式的影响。结果表明:射流进入RQL燃烧室后发生偏转且偏转方向和旋流方向有关,回流区长度、穿透深度和高湍动能区随着动量通量比的增大而增加;当J≥80时,淬熄射流下游出现高湍动能区,逐渐与上游融为一体;当J≥120时,回流区的长度基本不再发生明显变化。此外,非中心对冲结构C3具有更大的高湍动能区,掺混更均匀。

关键词：流场特性淬熄结构 RQL燃烧室动量通量比掺混特性

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燃气轮机中心分级燃烧器天然气掺氢燃烧的受迫振荡特性

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上海交通大学学报 2024年第3期58卷 304-311页

作者：史挺金明葛冰臧述升上海交通大学机械与动力工程学院上海200240

天然气掺氢燃烧是燃气轮机机组降低碳排放重要措施之一,但掺氢燃料的组分变化会导致燃烧室火焰结构及燃烧稳定性发生变化.为分析中心分级燃烧器掺氢燃烧条件下的燃烧不稳定性问题,通过试验研究了燃烧器入口速度扰动下,不同掺氢比对中心... 详细信息

天然气掺氢燃烧是燃气轮机机组降低碳排放重要措施之一,但掺氢燃料的组分变化会导致燃烧室火焰结构及燃烧稳定性发生变化.为分析中心分级燃烧器掺氢燃烧条件下的燃烧不稳定性问题,通过试验研究了燃烧器入口速度扰动下,不同掺氢比对中心分级掺氢燃烧的瞬态火焰结构、压力以及热释放响应的影响,并利用本征正交分解(POD)法提取了火焰脉动的特征模态,发现其主要包含火焰干涉区强脉动和轴向扰动两种模态.试验结果表明,随着掺氢体积比从0%增大到30%,火焰前沿向上游移动,两级火焰间距缩短,火焰干涉对应的脉动模态的能量占比增大,加强了压力与热释放的耦合,导致燃烧室内的压力响应增大9%,热释放响应增大37%.

关键词：中心分级燃烧器天然气掺氢受迫振荡本征正交分解

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涡轮静叶叶型对绝热气膜冷却效率的影响

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动力工程学报 2020年第10期40卷 793-800页

作者：韦景颖迟重然臧述升上海交通大学机械与动力工程学院上海200240

对燃气轮机涡轮叶片气膜孔进行参数化设计,分别在均匀加载和后加载导叶上布置了几何参数相同的全气膜冷却结构。采用数值模拟方法在不同供气压力和膨胀比下研究全气膜冷却特性,分析了叶型、供气压力和叶栅膨胀比等多因素对全气膜冷却效... 详细信息

对燃气轮机涡轮叶片气膜孔进行参数化设计,分别在均匀加载和后加载导叶上布置了几何参数相同的全气膜冷却结构。采用数值模拟方法在不同供气压力和膨胀比下研究全气膜冷却特性,分析了叶型、供气压力和叶栅膨胀比等多因素对全气膜冷却效率的影响。结果表明:压力面前缘区域(l_c≤0.4)的绝热气膜冷却效率和吹风比受冷气供气压力影响很大,压力面中下游(l_c>0.4)和吸力面的绝热气膜冷却效率受冷气供气压力影响较小;增大冷气供气压力会诱发强烈通道涡,在吸力面形成低冷却效率三角区;气膜冷却相似设计总体上是可行的,叶型变化引起的复合角性能差异是相似设计冷却效率差异的主要来源;膨胀比的改变对冷却性能影响不大,主要影响射流的吹风比。

关键词：涡轮静叶气膜冷却绝热气膜冷却效率相似设计数值模拟

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Effect of coating thickness on the calibration and measurement uncertainty of a wide-band liquid crystal thermography

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Chinese Optics Letters 2010年第4期8卷 395-397页

作者：饶宇藏述升万超一 Institute of Turbomachinery School of Mechanical and Power Engineering Shanghai Jiao Tong University

The liquid crystal thermography is a high-resolution and non-intrusive optical technique for full-field temperature *** present detailed calibration data for a wide-bandwidth thermochromic liquid crystal（TLC） to investigate the effect of the coating thickness on the hue-temperature characteristics and the measurement uncertainty of the *** is found that the coating thickness has appreciable effect on the TLC hue-temperature *** TLC coatings with the thickness over 20μm,a thicker TLC coating shows a relatively smaller measurement uncertainty,but the effect of the coating thickness is non-distinctive on the measurement uncertainty.

关键词： Calibration Coatings Liquid crystals Temperature Thermography (temperature measurement) Thickness measurement

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