矿井瓦斯抽采负压损失分析及对策

钻孔瓦斯抽采负压是影响瓦斯抽采效果的因素之一。针对矿井瓦斯抽采管路负压损失过大的问题,对某矿瓦斯抽采负压损失情况进行了分析,结果表明,管径变化、积水、漏气、管内异物、联网方式不合理等因素对瓦斯抽采负压损失均有影响,造成工作面钻孔抽采负压较小。根据抽采负压损失影响因素提出相应对策,对减小负压损失有重要意义。

基于负边距损失的小样本目标检测

现有的大部分目标检测算法都依赖于大规模的标注数据集来保证检测的正确率,但某些场景往往很难获得大量标注数据,且耗费大量人力、物力。针对这一问题,提出了基于负边距损失的小样本目标检测方法(NM‑FSTD),将小样本学习(FSL)中属于度量学习的负边距损失方法引入目标检测,负边距损失可以避免将同一新类的样本错误地映射到多个峰值或簇,有助于小样本目标检测中新类的分类。首先采用大量训练样本和基于负边距损失的目标检测框架训练得到具有良好泛化性能的模型,之后通过少量具有标签的目标类别的样本对模型进行微调,并采用微调后的模型对目标类别的新样本进行目标检测。为了验证NM‑FSTD的检测效果,使用MS COCO进行训练和评估。实验结果表明,所提方法AP_(50)达到了22.8%,与Meta R‑CNN和MPSR相比,准确率分别提高了3.7和4.9个百分点。NM‑FSTD能有效提高在小样本情况下对目标类别的检测性能,解决目前目标检测领域中数据不足的问题。

负顾客到达造成服务率变化的可修排队系统

为了解决由于在工作中操作失误引起机器服务速率减慢或是由于病毒入侵引起计算机速率减慢这一类问题,采用拟生灭过程和矩阵几何解的方法研究了具有正、负两类顾客服务速率可变的可修排队系统,其中负顾客到达带走正顾客的同时使服务速率减低.结果表明:负顾客到达率越高系统中平均等待的顾客数越少.给出了系统稳态平衡所需条件,推导出了系统稳态概率向量和系统的一些稳态排队和可靠性指标.最后给出了相关的数值实例为实际应用提供理论参考.

基于ε-Pinball损失函数的拉普拉斯双支持向量机

考虑到拉普拉斯双支持向量机中的平方损失函数对分类超平面两侧的同类样本点给予了相同重视,当出现噪声或离群点时,所得分类超平面可能会出现偏离的现象,为了减小噪声或离群点的影响,提出基于ε-Pinball损失函数的拉普拉斯双支持向量机;给出正、负损失的概念,探讨参数τ对分类超平面的影响,分析参数ν的意义,并进行数值实验。结果表明,通过调节参数τ,可增强模型的灵活性,使得模型具有较好的分类能力及抗噪性。

钻孔不同变形失稳时抽采负压分布规律研究

针对钻孔内瓦斯流动变质量流的特点及钻孔变形情况,建立了综合考虑钻孔负压动态变化的瓦斯抽采固-流耦合模型,并以新安煤矿为例,采用多物理场耦合软件Comsol Multiphysics对钻孔不同变形失稳时抽采负压分布进行了数值模拟研究。结果表明:①完整孔孔口、孔底附近煤层瓦斯分布基本相同,抽采负压损失较小。②钻孔塌孔时,仅塌孔段附近煤层瓦斯分布与完整孔稍有不同,总负压损失比完整孔大,但与孔口负压相比仍较小。③钻孔堵孔时,孔口、孔底周围煤层瓦斯分布差异巨大,钻孔有效抽采长度缩短,堵孔段附近煤层出现抽采空白带;完整段抽采压力变化相对较小且仍为负压,堵孔段抽采压力变成正值,且越靠近钻孔底部越接近附近煤层瓦斯压力。现场测试结果表明完整孔抽采负压损失较小,且随抽采时间的延长而变小,与数值模拟结果一致。

敞开式焙烧炉新型排烟架技术开发和应用

为解决敞开式焙烧炉传统排烟架压损大,压力分布不均的问题,通过开发新型排烟架,对排烟架的结构进行优化,保证排烟架内流场的均匀性,保证边火道的负压水平,从而降低排烟架压损。通过对新型排烟架的结构强度进行核验并对排烟架设备进行轻量化优化设计,做到了降低排烟架重量。生产实践采用新的排烟架技术,总管压力由-1200 Pa左右降低至-800 Pa左右,实现了节能降耗、提质增效目的。

油纸电容型套管缺油的危害及判断方法

通过解析油纸电容型套管的结构,介绍了套管四大组成部分的作用和原理,并重点阐述了套管内部绝缘介质的电气性能.同时指出了套管缺油的原因及危害,并说明了如何准确地判断缺油.通过实例阐述了套管缺油的查找方法,论证了综合利用电容量C、介质损失角tanδ、油中溶解气体色谱分析及红外线成像仪对发现套管缺油的合理性及准确性.

易腐性产品运输设施选择博弈

易腐性产品的价值会随着时间的流逝而逐渐损失,多个客户可以联合使用某种运输设施时,如何对费用进行公平且稳定的分摊是合作能否进行的基础.把易腐性产品的损失价值和运输费用之和作为总费用,进而将易腐性产品的运输设施选择的费用分配问题构造成运输设施选择合作博弈,证明了在易腐性产品负指数价值损失的情况下,运输设施选择博弈的核心非空,且为凹博弈,并讨论了解的特征.论文还证明具有附加运输费用的运输设施选择博弈的核心非空,分析了核心与线性规划松弛的对偶最优解之间的关系.论文对有约束设施选择博弈进行了分析,并提出了进一步研究的方向.

赵庄煤矿瓦斯抽采系统优化研究

为了解决赵庄煤矿瓦斯抽采系统负压、浓度、流量偏低的问题,基于图论、计算流体力学理论,将瓦斯抽采系统作为网络树图,利用矿井瓦斯抽采网络解算系统计算矿井瓦斯抽采系统负压损失地点及主要原因;通过优化赵庄煤矿瓦斯抽采系统的管网、抽采负压、管径等,以降低抽采系统负压损失、提升抽采率;并重新模拟赵庄煤矿瓦斯抽采系统管路与瓦斯抽采泵的连接方式,确定最优方案,提升孔口负压和瓦斯抽采量,为提高煤层瓦斯抽采效率提供理论基础。

基于流的遥感图像超分辨率重建

为了提高遥感图像超分辨率重建的质量,提出了一种基于流的遥感图像重建算法。首先,在Glow模型的基础上引入改进后的RRDB架构用于低分辨率图像特征提取,通过构建更多层和连接以提升训练的稳定性。然后,以一种纯数据驱动的流模型来训练分布的参数,通过最大化负的对数似然的方法进行优化,得到该算法的损失函数。实验证明该模型在网络训练过程中能够快速达到稳定收敛的状态,且具有很强的泛化能力。用重建出的图像质量对比SRCNN、SRGAN、ESRGAN,经过测试后发现,提出的算法远远优于SRCNN算法,与其他算法相比也有明显优势。重建出的图像不仅在指标上有所提升,例如与SRCNN相比,PSRN和SSIM分别提升了15%和40%,且人眼观察时有更高的清晰度,高频细节更为丰富。

真空度随真空管道长度变化规律研究

通过对PCB钻孔机抽真空设计的研究,借鉴流体力学理论中管道流体与管道摩擦模型,提出了真空度管道摩擦损失假设和管道真空负压损失摩擦系数,并推算出了实验管道的真空负压损失摩擦系数和真空负压随各种不同管径管道每米长度损失的计算公式,为PCB业界设计钻孔工序抽真空系统提供了具有实用价值的理论指导。

Evaluation of Loss of Load Probability and Expected Energy Generation in Multi-area Interconnected Systems with Wind Generating Units

Due to randomness of wind generator＇s availability, power system planners have big concern on EEG （expected energy generation） and system reliability of power system with wind generators. This paper presents a methodology to evaluate the EEG as well as overall LOLP （loss of load probability）, which is an index for system reliability of multi-area interconnected systems with wind generators, as well as conventional fossil fuel based generating units. The proposed model is also capable of tracking the energy export incorporating the multi-state probability model for wind generator which output varies with time and season.

Boundary layer separation control on a highly-loaded,low-solidity compressor cascade

Separated flow can be effectively controlled through the management of blade boundary layer development.Numerical simulations on a highly-loaded,low-solidity compressor cascade indicate that combined blowing and suction flow control technique can significantly improve cascade performance,especially in increasing the cascade loading and static pressure ratio as well as decreasing the loss coefficient.Meanwhile,it is more effective to improve cascade performance by blowing near leading edge on suction surface than suction near trailing edge.Both the locations and flow rates of blowing and suction are major impact factors of this method to cascade performance.Comparing to the baseline,the static pressure ratio increases by 15% and loss coefficient decreases by 80%,with a blowing fraction of 1.7% and a suction fraction of 1.38% of the inlet mass flow.

Experimental Research of Surface Roughness Effects on Highly-Loaded Compressor Cascade Aerodynamics

Aircraft engines deteriorate during continuous operation under the action of external factors including fouling, corrosion, and abrasion. The increased surface roughness of compressor passage walls limits airflow and leads to flow loss. However, the partial increase of roughness may also restrain flow separation and reduce flow loss. It is necessary to explore methods that will lower compressor deterioration, thereby improving the overall performance. The experimental research on the effects of surface roughness on highly loaded compressor cascade aerodynamics has been conducted in a low-speed linear cascade wind tunnel. The different levels of roughness are arranged on the suction surface and pressure surface, respectively. Ink-trace flow visualization has been used to measure the flow field on the walls of cascades, and a five-hole probe has been traversed across one pitch at the outlet. By comparing the total pressure loss coefficient, the distributions of the secondary-flow speed vector, and flow fields of various cases, the effects of surface roughness on the aerodynamics of a highly loaded compressor cascade are analyzed and discussed. The results show that adding surface roughness on the suction surface and pressure surface make the loss decrease in most cases. Increasing the surface roughness on the suction surface causes reduced flow speed near the blade, which helps to decrease mixing loss at the cascades outlet. Meanwhile, adding surface roughness on the suction surface restrains flow separation, leading to less flow loss. Various levels of surface roughness mostly weaken the flow turning capacity to various degrees, except in specific cases.

Prediction of Hub Corner Stall Characteristics of a Highly Loaded Low Speed Single Stage Fan

In this paper a numerical investigation has been presented on the stall mechanism of a highly loaded Single Stage Low Speed Fan designed for the research test facility to be installed at North Western Polytechnic University (NWPU) Xi’an, China. The results presented are for the design point, near stall and just stall operating conditions at design speed. Design point studies have been found to be an indicative of stall area. Unsteady method of domain scaling has been used to compute the results at near stall and just stall conditions. It has been found that unlike the conventional tip leakage flow of the rotor, stator hub section is mainly responsible for the stall of the fan. The flow mechanism has been discussed with correlation to the design variables and previous investigations. Commercial CFD code NUMECA FINE/Turbo has been used for computations; results have been compared with results obtained from commercial CFD code ANSYS-CFX. The loss prediction of latter code is conservative than the former. The stall mechanism predicted by both codes is analogous.

Investigation of Endwall Flow Behavior with Plasma Flow Control on a Highly Loaded Compressor Cascade

To discover the flow behavior in the endwall region and mechanism of plasma flow control on a highly loaded compressor cascade, distributions of static pressure coefficient, total pressure loss coefficient and streamline pat- tern were investigated. Results show that cross flow from the pressure surface to neighboring suction surface ex- ists under pitch-wise pressure gradient. The deflected endwall boundary layer flow interacts with the incoming flow, and then both of them leave off the endwall in tile form of a span-wise vortex. Effect of angle of attack on static pressure is greater than that of free stream velocity. The distinct variations of total pressure loss with end- wall actuations are mainly located within the outer verge of a triangular area with high total pressure loss. Effect of pitch-vAse actuation on separated flows is much better than that of stream-wise actuation, and both enhance with the increase of angle of attack and actuation strength. An efficient method for plasma flow control in the endwall region is the increase of actuation strength, such as adjusting discharge voltage or changing plasma power supply.

An Experimental Study of Separation Control on Ultra-Highly-Loaded Low Pressure Turbine Blade by Surface Roughness

An experimental study is conducted to improve an aft-loaded ultra-high-lift low pressure turbine(LPT) blade at low Reynolds number(Re) in steady state. The objective is to investigate the effect of blade roughness on the performance of LPT blade. The roughness is used as a passive flow control method which is to reduce total pressure loss and expand LPT operating margin. The experiment is performed on a low-speed cascade facility. 3 roughness heights and 3 deposit positions are investigated in the experiment which forms a large test matrix. A three-hole probe is used to detect flow aerodynamic performance and a hotwire probe is used to detect the characteristic of suction boundary layer. Regional roughness can suppress separation loss and bring fairly low turbulent dissipation loss. Detailed surveys near the blade surface shows that the loss reduction is due to the disappearance of separation bubble from the early transition onset.