A numerical simulation strategy for a compressor’s underlying axisymmetric characteristic and its application in body force model

Accurate prediction of the aerodynamic response of a compressor under inlet distortion is crucial for next-generation civil aircraft,such as Boundary Layer Ingestion(BLI)silent aircraft.Therefore,research on the Body Force(BF)model plays a significant role in achieving this objective.However,distorted inlet airflow can lead to varying operating conditions across different spatial locations of the compressor,which may cause some regions to operate outside the stability boundary.Consequently,the accuracy of BF model simulations might be compromised.To address this issue,this paper proposes a numerical simulation strategy for acquiring the steady axisymmetric three-dimensional flow field of a compressor operating at low mass flow rates,which is known as the Underlying Axisymmetric Pressure Rise Characteristic(UAPRC).The proposed simulation accounts for two different rotor speeds of a transonic compressor and identifies initial positions in the flow field where deterioration occurs based on prior experimental investigations.Moreover,simulation results are incorporated into the BF model to replicate hub instability observed in experiments.Obtained results demonstrate that this strategy provides valid predictions of the UAPRC of the compressor,thereby addressing the limitations associated with the BF model.

Impact of Controllable Factors on Export Performance of SMEs in Jordan

Exporting is of great interest for SMEs in Jordan from both microeconomic and macroeconomic perspective.The objective of this study was to identify to what extent specific internal factors contribute to export success of SMEs in Jordan.This study hypothesized that export performance of SMEs is directly affected by three groups of internal factors.These include firm characteristics,managerial characteristics,and marketing strategy.A multiple case approach is used to conduct this research and a structured interview is developed to collect the data directly from the participants.A pattern matching approach was used to test the hypotheses.The results show that export performance is positively affected by firm characteristics,managerial characteristics,and marketing strategy.Additionally,the demographic characteristics of managers and adaptation of distribution channels are unlikely to have an influence on export performance.This was unexpected,because of the plenty of empirical evidences in the literature that support the impact of these variables on export success.

Investigations of the effects of two typical jet crushing methods on the atomization and dust reduction performance of nozzles

Single-fuid nozzles and dual-fuid nozzles are the two typical jet crushing methods used in spray dust reduction. To distinguish the atomization mechanism of single-fuid and dual-fuid nozzles and improve dust control efciency at the coal mining faces, the atomization characteristics and dust reduction performance of the two nozzles were quantitatively compared. Results of experiments show that, as water supply pressure increased, the atomization angle of the swirl pressure nozzle reaches a maximum of 62° at 6 MPa and then decreases, but its droplet size shows an opposite trend with a minimum of 41.7 μm. The water supply pressure helps to improve the droplet size and the atomization angle of the internal mixing air–liquid nozzle, while the air supply pressure has a suppressive efect for them. When the water supply pressure is 0.2 MPa and the air supply pressure reaches 0.4 MPa, the nozzle obtains the smallest droplet size which is 10% smaller than the swirl pressure nozzle. Combined with the dust reduction experimental results, when the water consumption at the working surface is not limited, using the swirl pressure nozzle will achieve a better dust reduction efect. However, the internal mixing air–liquid nozzle can achieve better and more economical dust reduction performance in working environments where water consumption is limited.

EFFECT OF AXIAL SPACING ON COMPRESSOR STABILITY

Experimental studies are carried out at a low speed axial compressor with five different rotor/stator gaps. Analysis of the effect of axial spacing of two successive blade rows on the measured mean flow coefficient at stall inception and on the flow range of compressor under multi-cell rotating stall operating conditions proves that the stator can suppress the flow disturbance in the compressor and strengthen the stability of the compressor. Experimental data show that the stall flow coefficient decreases by reducing the axial spacing of successive blade rows. Moreover, by reducing the axial spacing, the stall pattern transition pace from multi-cell stall to single-cell stall can be shifted. And the compressor directly slips into single-cell stall at 21.0% CR axial spacing. By analyzing the pressure fluctuation closed to the surge line, it can be known that there exists an eigenfrequency where the amplitude of the oscillating pressure suddenly and dramatically increases as the compressor runs close to the surge line and this pressure disturbance is relevant to the compressor instability.

Experimental Studies on High-Frequency Performance of the Inverse Control Magneto-Rheological Damper

Severe vibration of underground structures may be induced under blast loads. According to the characteristics of the explosion-induced ground shock wave, a new-type damper, inverse control magneto-rheological（MR） damper was designed to control the vibration, The high-frequency performance test of the MR damper was carried out on the small shaking table. It is shown that the performance can be modeled by use of the modified Bouc-Wen model, and the Parameters of the model keep stable in the range of 15--50 Hz.

The Effect of Variable Stator on Performance of a Highly Loaded Tandem Axial Flow Compressor Stage

Increasing the aerodynamic load on compressor blades helps to obtain a higher pressure ratio in lower rotational speeds. Considering the high aerodynamic load effects and structural concerns in the design process, it is possible to obtain higher pressure ratios compared to conventional compressors. However, it must be noted that imposing higher aerodynamic loads results in higher loss coemcients and deteriorates the overall performance. To avoid the loss increase, the boundary layer quality must be studied carefully over the blade suction surface. Employment of advanced shaped airfoils （like CDAs）, slotted blades or other boundary layer control methods has helped the de- signers to use higher aerodynamic loads on compressor blades. Tandem cascade is a passive boundary layer control method, which is based on using the flow momentum to control the boundary layer on the suction surface and also to avoid the probable separation caused by higher aerodynamic loads. In fact, the front pressure side flow momentum helps to compensate the positive pressure gradient over the aft blade＇s suction side. Also, in compari- son to the single blade stators, tandem variable stators have more degrees of freedom, and this issue increases the possibility of finding enhanced conditions in the compressor off-design performance. In the current study, a 3D design procedure for an axial flow tandem compressor stage has been applied to design a highly loaded stage. Following, this design is numerically investigated using a CFD code and the stage characteristic map is reported. Also, the effect of various stator stagger angles on the compressor performance and especially on the compressor surge margin has been discussed. To validate the CFD method, another known compressor stage is presented and its performance is numerically investigated and the results are compared with available experimental results.

Aerodynamic Performance Improvement of a Highly Loaded Compressor Airfoil with Coanda Jet Flap

Coanda jet flap is an effective flow control technique,which offers pressurized high streamwise velocity to eliminate the boundary layer flow separation and increase the aerodynamic loading of compressor blades.Traditionally,there is only single-jet flap on the blade suction side.A novel Coanda double-jet flap configuration combining the front-jet slot near the blade leading edge and the rear-jet slot near the blade trailing edge is proposed and investigated in this paper.The reference highly loaded compressor profile is the Zierke&Deutsch double-circular-arc airfoil with the diffusion factor of 0.66.Firstly,three types of Coanda jet flap configurations including front-jet,rear-jet and the novel double-jet flaps are designed based on the 2D flow fields in the highly loaded compressor blade passage.The Back Propagation Neural Network(BPNN)combined with the genetic algorithm(GA)is adopted to obtain the optimal geometry for each type of Coanda jet flap configuration.Numerical simulations are then performed to understand the effects of the three optimal Coanda jet flaps on the compressor airfoil performance.Results indicate all the three types of Coanda jet flaps effectively improve the aerodynamic performance of the highly loaded airfoil,and the Coanda double-jet flap behaves best in controlling the boundary layer flow separation.At the inlet flow condition with incidence angle of 5°,the total pressure loss coefficient is reduced by 52.5%and the static pressure rise coefficient is increased by 25.7%with Coanda double-jet flap when the normalized jet mass flow ratio of the front jet and the rear jet is equal to 1.5%and 0.5%,respectively.The impacts of geometric parameters and jet mass flow ratios on the airfoil aerodynamic performance are further analyzed.It is observed that the geometric design parameters of Coanda double-jet flap determine airfoil thickness and jet slot position,which plays the key role in supressing flow separation on the airfoil suction side.Furthermore,there exists an optimal combination of front-jet and rear-jet mass flow ratios to achieve the minimum flow loss at each incidence angle of incoming flow.These results indicate that Coanda double-jet flap combining the adjust of jet mass flow rate varying with the incidence angle of incoming flow would be a promising adaptive flow control technique.

Impact of seismic excitation characteristics on the efficiency of tuned liquid column dampers

Various types of passive control systems have been used to suppress the seismic response of structures in recent years. Among these systems, Tuned Liquid Column Dampers （TLCDs） dissipate the input earthquake energy by combining the effects of the movement of the liquid mass in the container, the restoring force on the liquid due to the gravity loads and the damping due to the liquid movement through orifices. In this study, the effects of seismic excitation characteristics such as frequency content and soil condition on the seismic performance of TLCDs are investigated using nonlinear time-history analyses. In this regard, among the past earthquake ground motion records of Iran, 16 records with different parameters were selected. In the structural model developed, the attached TLCD is simulated as a Tuned Mass Damper （TMD） having the same vibration period and damping ratio as the original TLCD. The numerical results show that the seismic excitation characteristics have a substantial role on the displacement reduction capability of TLCDs and they should be considered accordingly in the design of TLCDs.

Performance analysis model for real-time Ethernet-based computer numerical control system

In order to optimize the embedded system implementation for Ethernet-based computer numerical control （CNC） system, it is very necessary to establish the performance analysis model and further adopt the codesign method from the control, communication and computing perspectives. On the basis of analyzing real-time Ethemet, system architecture, time characteristic parameters of control-loop ere, a performance analysis model for real-time Ethemet-based CNC system was proposed, which is able to include the timing effects caused by the implementation platform in the simulation. The key for establishing the model is accomplished by designing the error analysis module and the controller nodes. Under the restraint of CPU resource and communication bandwidth, the experiment with a case study was conducted, and the results show that if the deadline miss ratio of data packets is 0.2%, then the percentage error is 1.105%. The proposed model can be used at several stages of CNC system development.

Design and Prototyping of Micro Centrifugal Compressor for Ultra Micro Gas Turbine

In order to establish the design methodology of an ultra micro centrifugal compressor, which is the most important component of an ultra micro gas turbine unit, a 10 times size of the final target compressor （impeller outer diameter 40 mm, corrected rotational speed 220,000 r/min） was designed. The problems to be solved for downsizing were examined and a 2-dimensional impeller was chosen as the first model due to its productivity. The conventional 1D prediction method and CFD were used. The prototyped compressor was tested by using cold air at the reduced speed of 110,000 r/min. Following to the 10 times model, a 5 times size of the final target model having fully 3-dimensional shape （impeller outer diameter 20mm, corrected rotational speed 500,000 r/min） was designed and tested by using hot gas at the reduced speed of 250,000 r/min.

叶顶间隙对多级轴流压气机性能退化的影响

以某F级燃机压气机为研究对象,考虑燃机实际运行过程中腐蚀和磨损作用导致的压气机叶顶间隙变化,通过三维数值模拟方法开展了不同腐蚀/磨损状态下多级轴流压气机的性能退化机理研究,分析了叶顶间隙变化对多级轴流压气机性能的影响规律。结果表明:叶顶间隙增大会导致压气机特性曲线整体向质量流量减小的方向偏移,使得压气机的质量流量、效率及压比均产生一定程度的衰退;随着叶顶间隙的增大,压气机峰值效率逐渐降低,喘振裕度明显降低;叶顶间隙增大会导致压气机通道内的流动分离加剧,动叶叶顶间隙变化对压气机流动分离的影响更严重;静叶吸力面尾缘附近的流动分离导致形成低马赫数区,同时逆流的低速涡团导致叶根附近的损失显著增大,造成压气机性能衰退。

Prototyping of Ultra Micro Centrifugal Compressor-Influence of Meridional Configuration

In order to investigate the design method for a micro centrifugal compressor, which is the most important component of an ultra micro gas turbine, two types of centrifugal impeller with 2-dimensional blade were designed, manufactured and tested. These impellers have different shapes of hub on the meridional plane with each other. Moreover, these types of impeller were made for the 5 times and the 6 times size of the final target centrifugal impeller with the outer diameter of 4ram in order to assess the similitude for the impellers. The comparison among the performance characteristics of the impellers revealed the influence of the meridional configuration on the performance and the similitude of the compressors.

船用柴油机均值模型建模及仿真研究

柴油机模型的研究是探究柴油机性能、实现虚拟仿真的基础,可缩短仿真计算时间、有效节约柴油机开发成本。本文以RK270柴油机为研究对象,使用GT-POWER软件建立稳态性能仿真模型,在此基础上,采用仿真精度高、计算速度快的平均值法,以C++语言建立柴油机平均值模型,并归纳通用的平均值模型建模标定校核流程;提出二元响应拟合的方法,解决了涡轮增压器特性参数处理困难的问题,并借助数学工具,获得了压气机主要工作区域内拟合精度较高的模型。完成模型开发后,分析了8组工况下的仿真结果,通过误差分析,验证了模型的准确性,丰富完善了柴油机建模理论和方法,可应用于实时控制模型的动态仿真或者实现与船舶动力系统的交互。

基于双波长差示融合图谱的中药水红花子质量分析方法研究

该研究建立了以对照药材为基准物质定性和不依赖多种对照品定量的水红花子药材质量控制方法。采用高效液相色谱(HPLC)技术,结合双波长差示融合技术,以对照药材为基准物质建立水红花子的特征图谱,通过特征峰的标定明确药材真伪;对内标成分花旗松素进行准确定量,以花旗松素为基准计算各特征峰的相对含量,取“平均数-标准差”作为特征峰成分相对于内标物质化学成分的相对含量下限,依据相对含量下限明确水红花子药材的优劣。结果标定了水红花子特征图谱的10个共有特征峰,通过质谱(MS)鉴定出水红花子药材的7个成分,经对照品比对,指认特征峰中的3个化学成分分别为花旗松素、槲皮素和原儿茶酸,检测各批次药材中花旗松素的含量为0.5994%~0.7766%,规定了水红花子药材特征峰化学成分相对含量下限。该方法不依赖多种对照品,能清晰判断药材的真伪优劣,可为水红花子的质量控制提供参考。

叶顶间隙对离心压气机性能的影响机理研究

为明确叶顶间隙对离心压气机性能影响的机理,采用数值模拟方法对不同叶顶间隙尺寸下的离心压气机叶顶泄漏涡和流动损失进行了研究。首先,对实验结果与数值计算结果进行了对比,验证了数值模拟的可靠性;然后,分析了不同叶顶间隙下压气机等熵效率及压比的变化趋势;最后,对内部流动特性进行了分析,阐述了不同间隙下叶轮内部涡结构变化形态、泄漏流流线分布及沿流动方向的熵变化规律,揭示了不同叶顶间隙对压气机性能的影响机理。研究结果表明:叶顶间隙比从0.018增加到0.054时,全工况范围内效率下降最大变化量分别为0.7%、0.6%、0.4%及0.2%,压比整体下降幅度保持在0.3%左右。叶顶泄漏流与主流掺混形成叶顶泄漏涡和叶顶分离涡,其中叶顶泄漏涡是主要损失来源。随着叶顶间隙比增大,靠近叶片前缘20%流向范围内的流动损失变化较小,靠近叶片尾缘40%范围内的损失增大。叶顶间隙比增加导致泄漏涡尺寸增大从而降低有效过流面积,是造成压气机性能下降的主要原因。

大功率往复式压缩机管道振动原因及振动控制研究

大功率往复式压缩机在天然气生产和输送中具有重要作用,其安全性对于整个天然气系统的稳定至关重要。然而,该类压缩机在运行过程中产生的振动问题,不仅会降低其工作效率,还可能引发安全事故。文章分析了大功率往复式压缩机管道振动的原因,并提出了有效的控制措施,旨在保障天然气储气库的生产安全,提升压缩机运行效率。

大型透平压缩机多维度智能化管控技术应用

为了提高透平压缩机组控制的可辨识性、非稳态波动的抗干扰性,改善系统的稳定性,提出了大型透平压缩机的多维度智能化管控技术。该技术整合了所有数据的重要关联特征,并对各关联项尤其是强关联项进行分类提取和解析建模,生成关联因素矩阵进行计算比对及协调控制,并对重要独立变量进行数据特征放大回归线性分析,提前预见数据趋向特征,最终进行及时准确的主动性控制,避免问题及影响的不断放大,保证机组的稳定运行,实现大型透平压缩机的全局稳态化智能主动控制。

载荷分布规律对开槽压气机叶型气动性能的影响

航空压气机叶片通道内流动呈强逆压梯度,为了减小流动损失、扩大稳定工作范围,针对压气机静子叶型提出一种新型开槽叶片,槽道由叶片前缘进气吸力面出气,使用来流速度冲量有效抑制吸力面附面层的发展。采用计算机数值模拟方法,研究不同吸力面峰值等熵马赫数位置的可控扩散叶型开槽对叶栅气动性能的影响。研究结果表明:在设计工况下,开槽可有效抑制吸力面附面层发展,降低叶栅损失,增加气流转角;吸力面峰值等熵马赫数位置越向尾缘,在整个进气角范围内,开槽降低损失程度越大,并且由于攻角越大吸力面附面层越厚,开槽降低损失程度越大。

广陈皮高效液相色谱陈化特征图谱研究

【目的】建立广陈皮的高效液相色谱(HPLC)陈化特征图谱。【方法】采用HPLC-二极管阵列检测器(DAD)技术分析不同年份广陈皮之间的成分差异,测定各差异色谱峰的相对峰面积,通过聚类分析对其进行陈化等级分类,并通过中药色谱指纹图谱相似度评价系统(2012A版)进行评价。【结果】不同年份广陈皮被聚为Ⅰ、Ⅱ类两个不同的陈化等级,Ⅰ类(低陈化等级)广陈皮的相似度为0.708~0.957,Ⅱ类(高陈化等级)广陈皮的相似度为0.734~0.976,且两者之间的相似度均低于0.6。建立的特征图谱中存在9个差异色谱峰;Ⅱ类广陈皮的对照特征图谱T2可视为其陈化特征图谱,其中1~4号峰、9号峰为陈化特征峰。【结论】建立的广陈皮陈化特征图谱操作简单,具有良好的重复性与可靠性,可用于不同年份广陈皮的质量评价。

基于3维数值仿真的变循环压缩系统部件匹配分析

为了研究变循环压缩系统中各部件之间的匹配关系以及在整机调节时的表现,采用3维数值仿真软件对变循环发动机的风扇、核心机驱动风扇级(CDFS)、高压压气机和外涵道开展联合数值仿真,并对比数值计算与试验结果的差异。针对单、双涵工作模式,开展内、外涵出口节流特性计算,分析了内、外涵出口压力调节导致的各部件匹配关系的变化,获得了涵道比的变化范围以及极限调节状态下的各部件表现出的流动特征,确定了制约整个压缩系统喘振裕度的关键部件。结果表明:在双涵模式下,外涵节流导致风扇匹配点明显提高,首先到达喘振边界;在单涵模式下,外涵节流导致风扇和CDFS匹配点同时提高,几乎同时到达喘振边界;在单、双涵模式下,内涵节流均使高压压气机首先到达喘振边界。仿真得到的外涵道损失与试验偏差在4%以内。