分油器殼體注塑模具設(shè)計【含16張CAD圖紙】

喜歡就充值下載吧，，資源目錄下展示的全都有，，下載后全都有，dwg格式的為CAD圖紙，有疑問咨詢QQ：414951605 或1304139763 長春工程學院 2020屆畢業(yè)設(shè)計（論文）指導教師資格及題目審批表 指導教師姓名 王利濤 所在單位 機電學院機制教研室 指導教師職稱 副教授 所學專業(yè) 機制 設(shè)計（論文）題目 分油器殼體注塑模具設(shè)計 題 目 類 型 設(shè)計 √ 題 目 來 源 科 研 實驗室建設(shè) 論文 工程生產(chǎn) √ 自 擬 題目真實性程度 真實 √ 題目新舊 新題 難度 等級 難 一般 模擬 舊題 √ 較難 √ 設(shè)計（論文）地點 校內(nèi) √ 設(shè)計（論文）時間 自 03月2 日 至06 月12日 校外 題目概要（設(shè)計（論文）的目的、可行性、技術(shù)路線等）： 該題目來源于長春斯美克模具公司，分油器上殼體注塑模具設(shè)計是通過應用三維設(shè)計軟件結(jié)合專業(yè)知識完成一付完整注塑模具設(shè)計。通過該設(shè)計題目，使學生在塑件結(jié)構(gòu)工藝分析、塑件成型工藝分析、模具總體結(jié)構(gòu)方案論證與設(shè)計，模具零件結(jié)構(gòu)設(shè)計與計算、編寫技術(shù)文件、查閱文獻和三維設(shè)計軟件應用能力方面受到一次綜合訓練，鞏固和綜合運用所學知識，掌握正確設(shè)計思想與方法，培養(yǎng)學生的工程應用能力。 殼體外形復雜，不但有倒扣位，且有橫向油管結(jié)構(gòu)，分型面多且復雜，模具開模需進行斜導柱外抽芯滑塊設(shè)計或液壓輔助開模系統(tǒng)，要考慮模具結(jié)構(gòu)布局，模具設(shè)計總體難度較難。完成該畢業(yè)設(shè)計題目應具備上機條件和初步的三維軟件應用能力。 設(shè)計內(nèi)容（1）塑件結(jié)構(gòu)分析與成型工藝分析。（2）模具總體方案論證與成型設(shè)備的選用。（3）模具結(jié)構(gòu)設(shè)計與計算。包括分型面設(shè)計、凸凹模成型零件結(jié)構(gòu)設(shè)計與計算；斜導柱外抽芯滑塊結(jié)構(gòu)設(shè)計，澆注系統(tǒng)設(shè)計與計算、頂出機構(gòu)設(shè)計與計算、導向與定位機構(gòu)設(shè)計，模溫調(diào)節(jié)系統(tǒng)設(shè)計。（4）模具總體尺寸的確定，選擇校核模架。（5）成型設(shè)備的校核與模具檢查。（6）繪制模具結(jié)構(gòu)總裝圖和零件工作圖 塑件三維數(shù)據(jù)文件iges ；塑件精度等級MT5；批量生產(chǎn)10萬-15萬件/年；要求模具自動化程度高，產(chǎn)品表面光滑、無缺陷；模具與型腔表面垂直平整，不允許有拉傷痕跡，冷卻水道不允許有滲漏現(xiàn)象；各模板配合面四角應銑出拆模間隙。 注塑件零件圖（含三維圖）；模具總裝配圖（計算機出圖）；模具所有零件圖（計算機出圖）；設(shè)計圖紙數(shù)量不少于3張A0 圖紙；設(shè)計計算說明書1.5萬字不少于40頁；譯文與開題報告不少于3000字； 教研室意見： 教研室主任簽字： 2020年3月1 日 學院（系）審查意見： 院長（系主任）簽字： 年 月 日 備注：1.此表由擬擔任畢業(yè)設(shè)計（論文）指導工作的教師填寫，每個題目填報一張表，一式兩份； 2.部分分項填寫時，只在對應項內(nèi)打“√”即可； 3.表中真實題目是指在學校、生產(chǎn)、科研及其它單位實際立項的課題； 4.指導教師如果是外聘，應在所在單位欄中加注（外聘）字樣； 5.在畢業(yè)設(shè)計（論文）工作開始前，各院（系）將此表匯總，報教務處備案。 Journal of Harbin Institute of Technology(New series)哈爾濱工業(yè)大學學報(英文版)ISSN 1005-9113,CN 23-1378/T Journal of Harbin Institute of Technology(New series)網(wǎng)絡首發(fā)論 網(wǎng)絡首發(fā)論文文 題目：Nonlinear Pre-deformation Method for Compressor Rotor Blade 作者：Yongliang Wang，Shihao Li，Longkai Zheng，Da Kang 收稿日期：2020-01-10 網(wǎng)絡首發(fā)日期：2020-03-06 引用格式：Yongliang Wang，Shihao Li，Longkai Zheng，Da Kang Nonlinear Pre-deformation Method for Compressor Rotor Blade Journal of Harbin Institute of Technology(New series).網(wǎng)絡首發(fā)網(wǎng)絡首發(fā)：在編輯部工作流程中，稿件從錄用到出版要經(jīng)歷錄用定稿、排版定稿、整期匯編定稿等階段。錄用定稿指內(nèi)容已經(jīng)確定，且通過同行評議、主編終審同意刊用的稿件。排版定稿指錄用定稿按照期刊特定版式（包括網(wǎng)絡呈現(xiàn)版式）排版后的稿件，可暫不確定出版年、卷、期和頁碼。整期匯編定稿指出版年、卷、期、頁碼均已確定的印刷或數(shù)字出版的整期匯編稿件。錄用定稿網(wǎng)絡首發(fā)稿件內(nèi)容必須符合出版管理條例和期刊出版管理規(guī)定的有關(guān)規(guī)定；學術(shù)研究成果具有創(chuàng)新性、科學性和先進性，符合編輯部對刊文的錄用要求，不存在學術(shù)不端行為及其他侵權(quán)行為；稿件內(nèi)容應基本符合國家有關(guān)書刊編輯、出版的技術(shù)標準，正確使用和統(tǒng)一規(guī)范語言文字、符號、數(shù)字、外文字母、法定計量單位及地圖標注等。為確保錄用定稿網(wǎng)絡首發(fā)的嚴肅性，錄用定稿一經(jīng)發(fā)布，不得修改論文題目、作者、機構(gòu)名稱和學術(shù)內(nèi)容，只可基于編輯規(guī)范進行少量文字的修改。出版確認出版確認：紙質(zhì)期刊編輯部通過與中國學術(shù)期刊（光盤版）電子雜志社有限公司簽約，在中國學術(shù)期刊（網(wǎng)絡版）出版?zhèn)鞑テ脚_上創(chuàng)辦與紙質(zhì)期刊內(nèi)容一致的網(wǎng)絡版，以單篇或整期出版形式，在印刷出版之前刊發(fā)論文的錄用定稿、排版定稿、整期匯編定稿。因為中國學術(shù)期刊（網(wǎng)絡版）是國家新聞出版廣電總局批準的網(wǎng)絡連續(xù)型出版物（ISSN 2096-4188，CN 11-6037/Z），所以簽約期刊的網(wǎng)絡版上網(wǎng)絡首發(fā)論文視為正式出版。Journal of Harbin Institute of Technology(New Series)Received 2020-01-10.Sponsored by the National Natural Science Foundation of China(Grant No.51606023)and the Fundamental Research Funds for the Central Universities(Grant No.3132019204).*Corresponding author.E-mail:wangyl.DOI：10.11916/j.issn.1005-9113.19093 Nonlinear Pre-deformation Method for Compressor Rotor Blade Yongliang Wang*,Shihao Li,Longkai Zheng and Da Kang(Naval Architecture and Ocean Engineering College,Dalian Maritime University,Dalian 116026,China)Abstract:A cold compressor blade deforms elastically under aerodynamic and centrifugal loads during operation,transforming into a hot blade configuration.Blade deformation has a significant effect on the performance of compressor.A nonlinear pre-deformation method for compressor rotor blade was developed with consideration of the nonlinear features of blade stiffness and load which varies with blade configuration.In the blade profile design phase,the method can be used to compensate the aeroelastic deformation of the blade during operation.The adverse effects of blade deflection on compressor performance and structure can be avoided by the pre-deformation method.Due to the fact that the nonlinear method is sensitive to initial value,a load incremental method was applied to calculate initial blade deformation to stabilize and accelerate the pre-deformation method.The developed method was used to predict the manufactured configuration of the Stage 37 rotor blade.The variation rules of aerodynamic and structure parameters of the pre-deformed blade were analyzed under off-design conditions.Results show that the developed method ensures that under the design condition there was a good match between the actual blade configuration during operation and the intended design blade profile.The blade untwist angle of pre-deformed blade could be 0 at design point.Meanwhile,the tip clearance only decreased 0.2%.When the working speed was faster than 80%design speed,the performance of the pre-deformed blade agreed with that of the design blade.However,the mass flow rate and the total pressure ratio of the pre-deformed blade were lower at low speeds.Keywords:compressor blade;pre-deformation;blade reconstruction;fluid-structure interaction;blade deformation CLC number:V232.4 Document code:A 1 Introduction The blade of modern compressor is flat and thin,which shows a complicated external physical property and may even be produced using composite material and hollow-core construction.But all these improvements reduce the stiffness of the blade.Under operating condition,the blade of transonic compressor working with a high load will deform due to the effects of strong aerodynamic and centrifugal loads.The blade changes from the manufacturing configuration(cold blade shape)to the configuration under working speed and pressure ratio(hot blade shape).Research1-3 show that the parameters,such as tip clearance and flow angle,are influenced by miniscule changes of blade shape,causing differences of the flow in the compressor between the working and design conditions,thus influencing the overall performance of the gas turbine and potentially causing serious problems,such as a decline in aerodynamic stability4-5.To ensure the blade shape under working condition is the same as or similar to the best designed aerodynamic configuration,a pre-deformation method is used,which can obtain the cold blade shape for manufacturing by subtracting the blade deformation from the desired blade shape under hot running condition,i.e.“pre-deforming”the blade.However,the deformation of blades under different conditions are different due to varying stress conditions,so the hot blade shape under each off-design condition is not the same.To study the problems of the Published online：2020-03-06 11:45:22URL：Journal of Harbin Institute of Technology(New Series)compressor under off-design condition,such as aerodynamic performance and forced response of aeroelasticity and flutter6-8,after the cold blade shape is obtained through pre-deformation,it is necessary to start from the cold blade shape and construct the corresponding hot blade shape based on load characteristics under off-design conditions.This process is called the reconstruction of blade shape.Pre-deformation is a key link for implementation of the design configuration under design condition,as it ensures an ideal aerodynamic performance for the compressor.Reconstruction of blade shape is a significant pre-condition of test and analysis for the aerodynamic performance or strength and vibration characteristics of the high load compressor under off-design condition.Research on blade configuration have been done by many engineering researchers.Ohtsuka9 considered the effect of centrifugal force on torsional deformation of blade,and the calculated results are in a good agreement with the measured value from the rotating blade.However,the influence of aerodynamic force is not considered,and the fluid-structure interaction effect between blade and airflow is ignored.Liu10 indicated that the effect of aerodynamic force on deformation of the blade cannot be ignored because all the components of aerodynamic force have some effect on the torsional deformation of the blade,although the aerodynamic force size is an order of magnitude lower than the centrifugal force.Mahajan et al.11 proposed the transformation method of the cold and hot configuration of the blade,and the method was applied to research on the deformation of E3 fan blade by General Electric.Their research show that the temperature load has a weaker effect on blade deformation when compared with the aerodynamic force and centrifugal force.Timon et al.12 found that when rotating speed is higher than a certain critical value,the linear method will overestimate the deformation and cause a large error when calculating the deformation of the blade.Wang et al.13 studied the influence of static elastic deformation on the aerodynamic performance of NASAs Rotor 67.Results show that the main deformation of blade is the bending deformation under the action of aerodynamic force and centrifugal force.Under the near stall condition,the total pressure ratio of the hot blade is 1.8%more than the cold blade.Mao et al.14 carried out numerical analysis with the aerodynamic elasticity of the fan blade,which shows that ignoring aerodynamic elasticity can overestimate the structural safety of the blade.Zheng et al.15 gave a design method of blade untwist.The influences of material,aerodynamic condition,and rotating speed on deformation of blades and untwist design parameter were studied16,but this method requires confirmation of the optimum damping ratio,which increases the amount of computation.Pre-deformation designs of blades in existing research are usually based on linear method.However,almost all phenomena in solid mechanics are nonlinear.The stiffness matrix of the structure and the stress load are nonlinearly related to its geometrical configuration.In particular,the stress and geometry of the blade of a transonic compressor has a strong nonlinear dependency relationship.Thus,a high-precision solution should be obtained by nonlinear method.Existing literature only introduce the pre-deformation and blade reconstruction methods separately.However,the research on how the aerodynamic parameters and structure parameters change under off-design condition of pre-deformation blades is still lacking.In this study,a nonlinear pre-deformation design method is presented for compressor rotor blade,in which the effects of aerodynamic force and centrifugal force on blade deformation are considered.This method was applied to the pre-deformation design for the Stage 37 rotor blade.On this basis,the nonlinearity of load and stiffness in blade deformation process were considered,and the blade reconstruction of pre-deformation blade was done under off-design condition.Patterns of changes of aerodynamic Journal of Harbin Institute of Technology(New Series)performance and structure parameters of different blade configurations were analyzed under off-design condition.2 Pre-deformation Design Method for Blades 2.1 Pre-deformation Process The purpose of pre-deformation is to compensate the amount of deformation of the blade under working condition in design stage,thus the desired configuration of the compressor blade under the specified working condition is ensured.Fig.1 shows the iterative process of the pre-deformation design of a compressor blade.Structural SolverFluid SolverdesignXCentrifugal LoadAerodynamic Load0U11colddesigniiXXU=1iiUU=FalseIncremental Method1coldiX(1)(2)(3)(4)Blade Reconstruction1hotcoldiiiXXU=+111=hotdesigniiiiiXXUUUUTrue(5)Fig.1 Iterative process of blade pre-deformation The general idea is to pre-establish an assumed cold blade shape,calculate the assumed hot blade shape,which is deformed from the assumed cold blade shape,compare the deviation between the design blade shape and the assumed hot blade shape,and determine whether the deviation can meet precision requirements.If the deviation is satisfied,pre-deformation is completed.Otherwise,repeat the iterative process until convergence.Specific steps are as follows:1)Structural analysis software and fluid analysis software were used to analyze the design blade shape Xdesign,which was known,and to obtain centrifugal load and aerodynamic load under design condition.The load conditions were divided equally,and the level of load increment was m(m=10 was used).The generated equivalent node load condition was invoked by the load increment method.2)The design blade shape Xdesign was loaded by load increment method,and the initial node displacement U0 was calculated.3)Node displacement Ui-1 was set for the compensation dosage of pre-deformation(Ui-1=U0 was set for the first time iterative)and the new cold blade shapecolddesign11iiXXU=was calculated.4)NEWTON-RAPHSON iterating method was used,blade reconstruction was carried out on cold blade cold1iX under design condition,node displacement Ui was obtained,and the relevant assumed hot blade shape was hotcold1iiiXXU=+.5)According to pre-established convergence coefficient (in this study=10-3),infinite norm was used to judge whether convergence was satisfied or not.Convergence criterion was 11iiiUUU.If the convergence criterion was satisfied,output the node coordinate of cold bladecold1iX,or set Ui-1=Ui and repeat Step(3),(4),and(5)until it converged.2.2 Load Increment Method At the beginning of the pre-deformation design,a hypothetical cold blade shape is required as the initial condition.A good initial condition can improve the Journal of Harbin Institute of Technology(New Series)convergence speed of pre-deformation design.In this study,the load increment method was used to solve the initial deformation of the design blade of the compressor.The method is based on the basic concept of piecewise linear curve.The loading process diagram of load increment method is shown in Fig.2.In order to deal with the non-linear relationship between the load F and the displacement U,load was divided into several micro-increments Fi according to certain rules.Then the blade was loaded step by step,and each level of load increment could be approximated as a linear process.There were no strict limits on the division of load increment.The magnitude of the load increment at all levels could be equal or not,so long as the sum of all the increments at all levels was equal to the full load,which was 1miiFF=(m being the level of the load division).The final error of the load increment method is the result of accumulation of calculation error at all levels.Small incremental division can be helpful to improve calculation accuracy and convergence,but too much subdivision can result in a large increase in computing time.UFF3F2F1FO1F2F3FiF2U3U1UiU Fig.2 Load incremental method The specific iterative steps of incremental method are as follows:It was started with the design blade shape.The load increments from the first level to the last level were applied to the compressor blade step by step,and the displacement increment was obtained by solving the force balance equation11()iiiUK UF=.According to the current displacement results,the stiffness matrix of the blade was regenerated,and the next level of load increment Fi+1 was applied to solve the problem.Loading was repeated until the last level of load increment and the total deformation of the blade U was calculated.2.3 Reconstruction Method for Blade The key to the success of blade reconstruction is to determine the deformation amount of the cold blade shape under operation condition,so as to confirm the actual configuration and aerodynamic performance of the compressor blade under the operation condition.The pressure load of the compressor blade has a strong nonlinear dependency relationship with blade configuration.Therefore,blade reconstruction is aimed at calculating deformation of blade under the non-conservative force.An iterative method of non-conservative force,which is used in this study,is introduced as follows.Rotating blades deform under the combined action of aerodynamic force Fa and centrifugal force Fc.These two kinds of forces are a function of node displacement U.According to stress analysis for the blade of compressor,at the final equilibrium state,resultant force Fa+c of the aerodynamic force and centrifugal force is equal to the elastic restoring force Fe of the blade,i.e.Fa+c(U)=Fe(U).In the analysis of the non-conservative force problem,it is not only necessary to solve the displacement of blade nodes,but also to solve the aerodynamic force and centrifugal force of the blade.The schematic diagram of the non-conservative iterative method is shown in Fig.3.At the beginning of this process,Fa+c(U0)and K(U0)could be confirmed from the undeformed blade configuration.Then U1 was calculated.After the blade deformed,a new resultant force Fa+c(U1)was calculated to determine the unbalanced force Journal of Harbin Institute of Technology(New Series)F1=Fa+c(U1)-Fa+c(U0)of the system.The variable quantity of displacement U2 was confirmed according to stiffness matrix K(U1)obtained after deformation.By parity of reasoning,the variable quantity of displacement Ui was calculated by the unbalanced force Fi=Fa+c(Ui)-Fa+c(Ui-1)and stiffness matrix K(i),and the real solution was approximated by continuous iteration until the unbalanced force Fi was zero.As mentioned above,in solving the problem of non-conservative force,load force and stiffness matrix will be updated in every calculation step according to the variable quantity of node displacement in the last step.Hence,the nonlinear characteristics of load and stiffness matrix changing with variation configuration can be considered at the same time by using non-conservative iterative method.0()K UFU1UOerror()eeFF U=0()a cFU+1U1()a cFU+1F2U()a ciFU+iF2UiUiU()a ca cFFU+=1()K U()iK U Fig.3 The iterative method of non-conservative force(where Fa+c=Fa+c(U)is the combined force of aerodynamic and centrifugal loads,and Fe=Fe(U)is the elastic restoring force of the blade)The blade reconstruction method adopted in this paper is shown in Fig.4,and the solution process is as follows:1)It was started with the cold blade shape Xcold.Finite element analysis and flow field analysis were carried out using the cold blade shape,and centrifugal force and aerodynamic load F(Ui)were obtained.The unbalanced force of system Fi was the difference between F(Ui)and the load condition obtained at the last iteration F(Ui-1).For the first calculation,the stress load of Xcold was set as the unbalanced force of the system.2)Unbalanced force of the system Fi was added onto the blade shape to calculate the incremental quantity of displacement Ui+1 by structural analysis.3)Node coordinate of the assumed hot blade shape hotcold11iiXXU+=+was calculated.For the first calculation,U1=U1 was set.Structural SolverFluid SolvercoldXCentrifugal LoadAerodynamic LoadTrue1hotiX+Structural Solver1iU+1111iiihotcoldiiUUUXXU+=+=+1hotiX+False1iiUU+1()()iiiFF UF U=(1)(2)(3)(4)Fig.4 Iterative process of blade reconstruction 4)According to the pre-established convergence coefficient(=10-3),infinite norm was used to judge the convergence,and the convergence criterion was 1iiUU+.If convergence criterion was satisfied,output the node coordinate of hot bladehot1iX+,otherwise set the assumed hot blade shape hot1iX+as the current blade shape and repeat the above steps.Journal of Harbin Institute of Technology(New Series)3 Computational Model and Numerical Method In this study,the pre-deformation design and blade reconstruction calculation of Stage 37 rotor blades of the transonic compressor were carried out.The design speed of Stage 37 was 17188.7 RPM,the tip clearance of the rotor blade was 0.356 mm,the total pressure ratio was 2.050,the adiabatic efficiency was 0.842,the blade material was Maraging 200 whose elastic modulus was 210 GPa,Poissons ratio was 0.3,and the density was 8000 kg/m3.The specific design parameters and test data can be seen in Refs.17-18.Blade profile data given by Ref.17 was set as the design blade shape,and peak efficiency point at selected design speed was set as the design condition.The Stage 37 rotor blade was pre-deformed according to the stress condition of the design point.After obtaining the cold blade shape,the blade reconstruction calculation was carried out under the off-design condition.It must be noted that the stator blade was rigid enough to resist deformation.The rotor blade was the only concern when blade shape was converted,and pre-deformation and reconstruction calculation were not performed on the stator blades.Fig.5 shows the blade solid grid and fluid grid of stage.Static deformation of the moving blade was calculated by using ANSYS.A hexahedron grid was used in the finite element model of the moving blade,and the total number of solid grids was 11808.Fixed branch boundary was adopted in blade root.An O4H topological structure was adopted in fluid grid,and the total number of grids was 1339852.CFX was used in the steady numerical simulation of fluid domain,and the k-turbulence model was selected.The blending plane method was used in dealing with the junction of dynamic and static domain.The inlet total pressure and inlet total temperature of the boundary conditions were set,and the flow field results of different working conditions were adjusted by changing the backpressure of the outlet.The transfer of solid deformation to the flow field grid was realized by means of dynamic mesh technique.In order to ensure the quality of fluid grid,the grids of zone on the moving blade near to casing were set as rotating surface.(a)Solid grid of the rotor blade (b)Fluid grid with rotor blade(left)and stator blade(right)Fig.5 Computational grid 4 Results Analysis To verify the re