Propulsion and Power Research最新文献_第10页

Effect of hole arrangement patterns on the leakage and rotordynamic characteristics of the honeycomb seal 孔布置方式对蜂窝密封泄漏及转子动力特性的影响

IF 5.3 2区工程技术

Propulsion and Power Research Pub Date : 2022-06-01 DOI: 10.1016/j.jppr.2022.03.002

Wanfu Zhang, Chengjing Gu, Xingchen Yang, Kexin Wu, Chun Li

{"title":"Effect of hole arrangement patterns on the leakage and rotordynamic characteristics of the honeycomb seal","authors":"Wanfu Zhang, Chengjing Gu, Xingchen Yang, Kexin Wu, Chun Li","doi":"10.1016/j.jppr.2022.03.002","DOIUrl":"10.1016/j.jppr.2022.03.002","url":null,"abstract":"<div><p>The honeycomb seal is a vital component to reduce the leakage flow and improve the system stability for the turbomachines. In this work, a three-dimensional model is established for the interlaced hole honeycomb seal (IHHCS) and the non-interlaced hole honeycomb seal (NIHHCS) to investigate its leakage and rotordynamic characteristics by adopting computational fluid dynamics (CFD). Results show that the hole arrangement patterns have little impact on the pressure drop and turbulence kinetic energy distribution for the seals, and the IHHCS possesses a slightly lower leakage flow rate than the NIHHCS. Moreover, the numerical results also show that the NIHHCS possesses a better rotordynamic performance than the IHHCS at all investigated conditions. Both seals show a larger <em>k</em> and a lower <em>C</em><sub>eff</sub> with the increase of the positive preswirl ratios and rotational speeds, while the negative preswirl ratios would reduce the <em>k</em> and improve the <em>C</em><sub>eff</sub>. The NIHHCS possesses a higher absolute value of <em>F</em><sub>t</sub> for all operating conditions, this could explain the distinction of <em>C</em><sub>eff</sub> for both seals at different working conditions.</p></div>","PeriodicalId":51341,"journal":{"name":"Propulsion and Power Research","volume":"11 2","pages":"Pages 181-195"},"PeriodicalIF":5.3,"publicationDate":"2022-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S2212540X22000359/pdfft?md5=3f07e877429c897eda994b0d2ed15009&pid=1-s2.0-S2212540X22000359-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41628039","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 3

Thermal radiation effect on unsteady three-dimensional MHD flow of micropolar fluid over a horizontal surface of a parabola of revolution 微极流体在旋转抛物线水平面上非定常三维MHD流动的热辐射效应

IF 5.3 2区工程技术

Propulsion and Power Research Pub Date : 2022-03-01 DOI: 10.1016/j.jppr.2022.01.001

S.R.R. Reddy , P. Bala Anki Reddy

{"title":"Thermal radiation effect on unsteady three-dimensional MHD flow of micropolar fluid over a horizontal surface of a parabola of revolution","authors":"S.R.R. Reddy , P. Bala Anki Reddy","doi":"10.1016/j.jppr.2022.01.001","DOIUrl":"10.1016/j.jppr.2022.01.001","url":null,"abstract":"<div><p>This paper explores the time-dependent magnetohydrodynamics (MHD) micropolar fluid flow over a three-dimensional variable stretching surface in the occurrence of radiation effect. The model time-dependent partial differential equations (PDE's) in three independent variables are transformed into ordinary differential equations (ODE's) by the suitable self-similarity variables. Homotopy perturbation method (HPM) and Runge-Kutta (RK) 4<sup>th</sup> order method along with shooting technique are used in the present model. And also, HPM results are compared with Runge-Kutta (RK) 4<sup>th</sup> order method along with the shooting technique. The velocity, micro rotation in <em>x</em> and <em>y</em> directions, temperature, skin friction factor and heat transfer rates are examined for the emerging parameters. The velocity profiles and momentum boundary layer thickness intensification with increasing values of the vortex viscosity parameter. The higher value of a magnetic parameter declines the skin friction coefficient. This type of investigation may be profitable to the polymer fluids, exotic lubricants, electronic chips, artificial fibers, drawing of copper wires, etc.</p></div>","PeriodicalId":51341,"journal":{"name":"Propulsion and Power Research","volume":"11 1","pages":"Pages 129-142"},"PeriodicalIF":5.3,"publicationDate":"2022-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S2212540X22000219/pdfft?md5=7a420dbe402c2ce1ad0e5c7d4d4f476d&pid=1-s2.0-S2212540X22000219-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45488927","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 20

A comprehensive physical insight about thermo physical aspects of Carreau fluid flow over a rotated disk of variable thickness by implementing finite difference approach 利用有限差分方法全面了解Carreau流体在变厚度旋转圆盘上流动的热物理方面

IF 5.3 2区工程技术

Propulsion and Power Research Pub Date : 2022-03-01 DOI: 10.1016/j.jppr.2022.03.001

Sardar Bilal, Imtiaz Ali Shah

{"title":"A comprehensive physical insight about thermo physical aspects of Carreau fluid flow over a rotated disk of variable thickness by implementing finite difference approach","authors":"Sardar Bilal, Imtiaz Ali Shah","doi":"10.1016/j.jppr.2022.03.001","DOIUrl":"10.1016/j.jppr.2022.03.001","url":null,"abstract":"<div><p>Present communication is devoted to analyze thermal characteristics of Carreau liquid flowing on variably thickened non-uniformly rotating disk. Mathematical formulation is constructed in view of complex coupled partial differential system. Afterwards, boundary layer approach is executed for comprehensive examination of under consideration phenomenon with in boundary layer region. Karman's transformation is capitalized to convert the attained PDE's into ordinary differential equations system. Solution of attained ODE's system is solved numerically by implementing Keller-Box scheme. Influence of protuberant involved parameters on momentum and thermal distributions is illustrated through sketches. In addition, impact of flow concerning parameters on wall shear stress and thermal flux is also evaluated. The assurance of present finding is done by making agreement with published results and by restricting considered problem to Newtonian case. Here, we observed that radially and tangentially directed wall drag lessen with growing magnitude of power law exponent index. Moreover, the consequence of disk thickness parameter grows stresses along radial direction whereas opposite behavior is depicted in case of tangentially directed friction and heat flux factors.</p></div>","PeriodicalId":51341,"journal":{"name":"Propulsion and Power Research","volume":"11 1","pages":"Pages 143-153"},"PeriodicalIF":5.3,"publicationDate":"2022-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S2212540X22000207/pdfft?md5=1465e13e4d5c31df84656ab3b5b886fe&pid=1-s2.0-S2212540X22000207-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46176959","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 8

Magneto-Soret-Dufour thermo-radiative double-diffusive convection heat and mass transfer of a micropolar fluid in a porous medium with Ohmic dissipation and variable thermal conductivity 具有欧姆耗散和变导热系数的多孔介质中微极流体的磁-索-杜弗热辐射双扩散对流传热传质

IF 5.3 2区工程技术

Propulsion and Power Research Pub Date : 2022-03-01 DOI: 10.1016/j.jppr.2022.02.001

Dulal Pal , Bhuban Chandra Das , Kuppalapalle Vajravelu

引用次数: 8

Recent research progress on airbreathing aero-engine control algorithm 吸气式航空发动机控制算法的研究进展

IF 5.3 2区工程技术

Propulsion and Power Research Pub Date : 2022-03-01 DOI: 10.1016/j.jppr.2022.02.003

Chengkun Lv, Juntao Chang, Wen Bao, Daren Yu

{"title":"Recent research progress on airbreathing aero-engine control algorithm","authors":"Chengkun Lv, Juntao Chang, Wen Bao, Daren Yu","doi":"10.1016/j.jppr.2022.02.003","DOIUrl":"10.1016/j.jppr.2022.02.003","url":null,"abstract":"<div><p>Airbreathing aero-engines are regarded as excellent propulsion devices from ground takeoff to hypersonic flight, and require control systems to ensure their efficient and safe operation. Therefore, the present paper aims to provide a summary report of recent research progress on airbreathing aero-engine control to help researchers working on this topic. First, five control problems of airbreathing aero-engines are classified: uncertainty problem, multi-objective and multivariable control, fault-tolerant control, distributed control system, and airframe/propulsion integrated control system. Subsequently, the research progress of aircraft gas turbine engine modelling, linear control, nonlinear control, and intelligent control is reviewed, and the advantages and disadvantages of various advanced control algorithms in aircraft gas turbine engines is discussed. Third, several typical hypersonic flight tests are investigated, and the modelling and control issues of dual-mode scramjet are examined. Fourth, modelling, mode transition control and thrust pinch control for turbine-based combined cycle engines are introduced. Followed, significant hypersonic airframe/propulsion integrated system control is analysed. Finally, the study provides specific control research topics that require attention on airbreathing aero-engines.</p></div>","PeriodicalId":51341,"journal":{"name":"Propulsion and Power Research","volume":"11 1","pages":"Pages 1-57"},"PeriodicalIF":5.3,"publicationDate":"2022-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S2212540X22000177/pdfft?md5=134268803e0df9a61ec8c78748dcedd2&pid=1-s2.0-S2212540X22000177-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41315928","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 24

Investigation on C2H4-Air combustion mode in a non-premixed rotating detonation combustor c2h4 -空气在非预混旋转爆震燃烧室燃烧模式的研究

IF 5.3 2区工程技术

Propulsion and Power Research Pub Date : 2022-03-01 DOI: 10.1016/j.jppr.2022.02.002

Shengbing Zhou , Hu Ma , Yuan Ma , Changsheng Zhou , Ning Hu

{"title":"Investigation on C2H4-Air combustion mode in a non-premixed rotating detonation combustor","authors":"Shengbing Zhou , Hu Ma , Yuan Ma , Changsheng Zhou , Ning Hu","doi":"10.1016/j.jppr.2022.02.002","DOIUrl":"10.1016/j.jppr.2022.02.002","url":null,"abstract":"<div><p>Based on the working characteristics of the rotating detonation combustor, the combustion mode of C<sub>2</sub>H<sub>4</sub>-Air under non-premixed injection conditions is experimentally studied in this paper. By changing the equivalence ratio, we observed the acoustic deflagration mode, fast deflagration mode, stable detonation mode, and weak detonation mode in the combustor. The velocity and pressure of the shock wave increase gradually as the equivalence ratio increases from 0.6 to 1.8. The stable detonation region appears near the stoichiometric ratio and the velocity of the detonation wave is relatively stable. When the equivalence ratio of the mixture is larger than 1.32, the stable detonation wave will suddenly extinguish, forming a weak detonation mode until the end of the combustor operation. The combustion mode of weak detonation is greatly affected by the fuel injection pressure ratio, and the release rate of energy is the main reason for the formation of deflagration mode or detonation mode.</p></div>","PeriodicalId":51341,"journal":{"name":"Propulsion and Power Research","volume":"11 1","pages":"Pages 85-96"},"PeriodicalIF":5.3,"publicationDate":"2022-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S2212540X22000153/pdfft?md5=9f53b2cc9df2a4024e89d89ed43482e0&pid=1-s2.0-S2212540X22000153-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48435963","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

Transient Dean flow in a composite annular duct with porous walls partially filled with porous material 多孔壁部分填充多孔材料的复合环形管道中的瞬态Dean流

IF 5.3 2区工程技术

Propulsion and Power Research Pub Date : 2022-03-01 DOI: 10.1016/j.jppr.2021.12.004

Basant K. Jha, Taiwo S. Yusuf

{"title":"Transient Dean flow in a composite annular duct with porous walls partially filled with porous material","authors":"Basant K. Jha, Taiwo S. Yusuf","doi":"10.1016/j.jppr.2021.12.004","DOIUrl":"10.1016/j.jppr.2021.12.004","url":null,"abstract":"<div><p>This work presents a semi-analytical solution of transient Dean flow in a composite annular duct with porous walls partially filled with porous materials. The flow is set up as a result of the imposed pressure gradient in the azimuthal <span><math><mrow><mo>(</mo><mi>θ</mi><mo>)</mo></mrow></math></span> direction while both the outer and the inner cylinders are fixed. The appropriate governing equations for the flow are rendered dimensionless and transformed using suitable techniques, the Laplace transform technique is further used to transform the partial differential equations into the total differential equation. The solution of the ODE is later transformed to the time domain using the well-known Riemann-sum approximation approach. To validate the accuracy of the numerical scheme deployed in this research, numerical comparison of the steady-state solution, and the values generated using the implicit finite difference on the transient state model is presented. Generally, higher dominance of clear fluid and fluid injection at the inner cylinder is found to enhance the fluid velocity at the fluid interface. It is also good to note that injection of fluid at the inner cylinder pose a decreasing influence on the flow with minimum or no effect near the point <em>R</em> = 1.7.</p></div>","PeriodicalId":51341,"journal":{"name":"Propulsion and Power Research","volume":"11 1","pages":"Pages 118-128"},"PeriodicalIF":5.3,"publicationDate":"2022-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S2212540X22000165/pdfft?md5=9197d3557a8f7753e7d4ab9abbc1d39d&pid=1-s2.0-S2212540X22000165-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48132060","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 2

Impact of nanoparticle shape on thermo-solutal buoyancy induced lid-driven-cavity with inclined magnetic-field 倾斜磁场下纳米颗粒形状对热溶质浮力诱导的盖驱动腔的影响

IF 5.3 2区工程技术

Propulsion and Power Research Pub Date : 2022-03-01 DOI: 10.1016/j.jppr.2022.01.002

Ratnadeep Nath, Krishnan Murugesan

{"title":"Impact of nanoparticle shape on thermo-solutal buoyancy induced lid-driven-cavity with inclined magnetic-field","authors":"Ratnadeep Nath, Krishnan Murugesan","doi":"10.1016/j.jppr.2022.01.002","DOIUrl":"10.1016/j.jppr.2022.01.002","url":null,"abstract":"<div><p>The aim of this paper is to numerically investigate the influence of nanoparticles shape on heat and mass transport phenomena in a moving lid cavity under the combined effect of thermo-solutal buoyancy force and magnetic force. The governing equations are transformed into velocity-vorticity form of equations and solved using Galerkin's weighted residual finite-element-technique. The analysis has been carried out with parameters like buoyancy ratio (−5 ≤ <em>N</em> ≤ 5), magnetic field inclination angle (0° ≤ <em>ϕ</em> ≤ 90°) with four shapes of Al<sub>2</sub>O<sub>3</sub> nanoparticle like bricks, blades, platelets and cylinders. The results revealed that the shape factor on Nusselt number is significant depending upon the inclined magnetic field and buoyancy ratio whereas on mass transfer the shape effect is negligible. The diffusion mode of transport process is stronger than the convection mode at higher inclination angle of magnetic field. Based on a given value of <em>N</em> and <em>ϕ</em>, blade and cylinder shows the best performance in Nusselt and Sherwood number respectively except the platelet shape that shows maximum frictional loss in terms of wall shear stress.</p></div>","PeriodicalId":51341,"journal":{"name":"Propulsion and Power Research","volume":"11 1","pages":"Pages 97-117"},"PeriodicalIF":5.3,"publicationDate":"2022-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S2212540X22000220/pdfft?md5=49231c7d37782b1a19a22f908e54c25c&pid=1-s2.0-S2212540X22000220-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42483010","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 2

Ground and flight tests of AlSat-1B butane propulsion system AlSat-1B丁烷推进系统的地面和飞行试验

IF 5.3 2区工程技术

Propulsion and Power Research Pub Date : 2022-03-01 DOI: 10.1016/j.jppr.2022.02.005

D. Darfilal , D. Gibbon

{"title":"Ground and flight tests of AlSat-1B butane propulsion system","authors":"D. Darfilal , D. Gibbon","doi":"10.1016/j.jppr.2022.02.005","DOIUrl":"10.1016/j.jppr.2022.02.005","url":null,"abstract":"<div><p>On September 26, 2016 Algerian Space Agency launched AlSat-1B, the second in a series of medium resolution earth observation satellites mission. AlSat-1B electro-thermal propulsion system follows the classic design principle that has been used on previous SSTL-100 missions. With a total dry weight of 5.17 kg, the system is filled with 2.35 L self-pressurized butane. The thruster assembly is designed to use 15 W (at 28 V) redundant heater elements, it is designed to have an average mission thrust of 50 mN. With a warm up time of 10 min, the temperature of the butane will be increased by over 250 °C. This is the equivalent of about 35% gain in specific impulse over ambient temperature butane. The spacecraft dry weigh at launch site was 107 kg, the propulsion system is designed to provide at least 19 m/s Delta-v to meet the spacecraft's mission requirement. To investigate the system readiness for flight, a series of performance tests have been completed at the Surrey Satellite Technology Ltd laboratories (United Kingdom), Satellite Development Centre (Algeria) and Satish Dhawan Space Centre rocket launch site (India), the results of these tests as well as initial flight test results are presented in this paper.</p></div>","PeriodicalId":51341,"journal":{"name":"Propulsion and Power Research","volume":"11 1","pages":"Pages 74-84"},"PeriodicalIF":5.3,"publicationDate":"2022-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S2212540X22000190/pdfft?md5=579184d76926c7d788800977c540f7a0&pid=1-s2.0-S2212540X22000190-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41288401","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Effect of high-pressure detonation products on fuel injection and propagation characteristics of detonation wave 高压爆轰产物对燃油喷射及爆轰波传播特性的影响

IF 5.3 2区工程技术

Propulsion and Power Research Pub Date : 2022-03-01 DOI: 10.1016/j.jppr.2021.12.003

Gaoyang Ge , Li Deng , Hu Ma , Zhenjuan Xia , Xiao Liu , Changsheng Zhou

{"title":"Effect of high-pressure detonation products on fuel injection and propagation characteristics of detonation wave","authors":"Gaoyang Ge , Li Deng , Hu Ma , Zhenjuan Xia , Xiao Liu , Changsheng Zhou","doi":"10.1016/j.jppr.2021.12.003","DOIUrl":"10.1016/j.jppr.2021.12.003","url":null,"abstract":"<div><p>The effect of high-pressure detonation products on fuel injection and propagation characteristics of detonation wave has been investigated in the form of ion voltage by varying the equivalence ratio (<em>ER</em>), air mass flux, and operation duration with hydrogen-air mixtures. It has been shown experimentally that the ion voltage decays gradually during the initial stage of rotating detonation wave (RDW). The attenuation of ion voltage is a general phenomenon, and the decay rate of ion voltage and its peak value of the trough state are related to the equivalence ratio and air mass flux. The analysis of interaction between the combustor and hydrogen plenum indicates that the feedback of high-pressure detonation products leads to the attenuation of ion voltage. In addition, the long-duration tests show that the ion voltage will recover to a steady state with the extension of reaction time, when the purgation (products leaving plenums) of detonation products is greater than feedback (products entering plenums) of detonation products in the hydrogen plenum. The recovery of ion voltage starts earlier at the higher equivalence ratio and air mass flux, and the peak value of ion voltage in the steady state also increases with the increase of equivalence ratio and air mass flux. A low frequency oscillation about 10–12 Hz occurs in the RDW at some operation conditions. This low frequency oscillation is related to the interaction between the combustor and hydrogen plenum, and can be eliminated by either increasing the equivalence ratio or decreasing the air mass flux.</p></div>","PeriodicalId":51341,"journal":{"name":"Propulsion and Power Research","volume":"11 1","pages":"Pages 58-73"},"PeriodicalIF":5.3,"publicationDate":"2022-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S2212540X22000141/pdfft?md5=98040146703f9ef4842bd5dbdcb3e33e&pid=1-s2.0-S2212540X22000141-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45289597","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1