本文選題：轉(zhuǎn)子 + 疲勞損傷��； 參考：《燕山大學(xué)》2016年博士論文

【摘要】：大型壓縮機(jī)屬于重大裝備機(jī)械,廣泛應(yīng)用于冶金、化工、電力等國(guó)家經(jīng)濟(jì)支柱產(chǎn)業(yè)及國(guó)防軍工領(lǐng)域,是衡量著一個(gè)國(guó)家工業(yè)發(fā)展水平的標(biāo)志性設(shè)備之一。壓縮機(jī)轉(zhuǎn)子由主軸和葉輪兩部分組成,是保證壓縮機(jī)組穩(wěn)定運(yùn)行的關(guān)鍵部件。目前制約我國(guó)再制造發(fā)展的核心問題是再制造基礎(chǔ)研究不足,必須解決再制造對(duì)象的疲勞失效機(jī)理、壽命演變規(guī)律和壽命預(yù)測(cè)等專屬問題才能高質(zhì)量的實(shí)現(xiàn)再制造。本課題以高附加值的轉(zhuǎn)子為研究對(duì)象,系統(tǒng)研究轉(zhuǎn)子主軸和葉輪的疲勞失效機(jī)理,建立再制造壽命預(yù)測(cè)模型,對(duì)豐富轉(zhuǎn)子疲勞基礎(chǔ)研究和推動(dòng)再制造產(chǎn)業(yè)的工業(yè)化發(fā)展具有重大意義。轉(zhuǎn)子在服役過程中的疲勞損傷機(jī)理與壽命演變規(guī)律的研究是轉(zhuǎn)子再制造的前提和基礎(chǔ)。由于轉(zhuǎn)子尺寸的限制和工況的復(fù)雜,使得常規(guī)試驗(yàn)方法很難準(zhǔn)確的對(duì)實(shí)際工況下轉(zhuǎn)子內(nèi)部應(yīng)變變化進(jìn)行量化,從而分析研究其疲勞失效機(jī)理和壽命演變規(guī)律。本文利用有限元法,對(duì)轉(zhuǎn)子的幾何形狀,邊界條件、載荷條件進(jìn)行合理簡(jiǎn)化,通過精確建模和網(wǎng)格劃分技術(shù)對(duì)轉(zhuǎn)子主軸和葉輪進(jìn)行分析。分析了滾動(dòng)接觸下主軸內(nèi)部的應(yīng)力應(yīng)變分布狀態(tài),確定了主軸的疲勞損傷機(jī)理;分析了特征載荷(離心力載荷、氣流載荷、振動(dòng)載荷等)非正常協(xié)同作用對(duì)葉輪疲勞損傷和壽命演變規(guī)律的影響,同時(shí)也對(duì)工藝載荷和極端工況載荷對(duì)轉(zhuǎn)子壽命的影響進(jìn)行了探討和研究,這些研究為葉輪再制造提供了理論基礎(chǔ)。以主軸的接觸疲勞失效為主軸再制造主要研究方向,基于等離子噴涂技術(shù)的高效性和低成本性,采用超音速等離子噴涂技術(shù)為轉(zhuǎn)子中主軸的關(guān)鍵再制造技術(shù),通過正交法確定最優(yōu)工藝參數(shù),利用超音速等離子噴涂得到質(zhì)量較好的主軸再制造涂層,利用課題組內(nèi)的新型滾滑接觸疲勞試驗(yàn)機(jī)得到了模擬工況下疲勞損傷試樣形貌,利用SEM對(duì)不同失效形貌進(jìn)行表征,以大樣本統(tǒng)計(jì)方法對(duì)涂層的失效模式進(jìn)行分類,系統(tǒng)研究不同接觸應(yīng)力水平下的涂層接觸疲勞失效機(jī)理,通過P-S-N曲線建立了主軸再制造的接觸疲勞壽命模型。針對(duì)葉輪復(fù)雜的尺寸和結(jié)構(gòu)特點(diǎn),對(duì)葉輪的危險(xiǎn)結(jié)構(gòu)部位進(jìn)行力學(xué)和結(jié)構(gòu)的相似簡(jiǎn)化處理,確定出能夠代表葉輪危險(xiǎn)結(jié)構(gòu)的試件形式與尺寸,基于試件尺寸和形式研制和搭建了能夠模擬葉輪實(shí)際工況條件的綜合試驗(yàn)平臺(tái)。研究了葉輪構(gòu)件的疲勞失效機(jī)理并建立了葉輪構(gòu)件的壽命預(yù)測(cè)模型�；诰C合試驗(yàn)平臺(tái)和葉輪材料試樣,對(duì)模擬工況下的葉輪構(gòu)件失效形式和機(jī)理進(jìn)行分類和表征,并對(duì)預(yù)測(cè)葉輪構(gòu)件疲勞極限的Soderberg曲線進(jìn)行了修正和試驗(yàn)驗(yàn)證。以多軸疲勞模型為理論基礎(chǔ),對(duì)多軸疲勞壽命預(yù)測(cè)的經(jīng)驗(yàn)和半經(jīng)驗(yàn)公式方法:基于最大主應(yīng)變的多軸等效應(yīng)變疲勞壽命預(yù)測(cè)方法、基于等效應(yīng)變的多軸等效應(yīng)變疲勞壽命預(yù)測(cè)方法和基于最大剪切應(yīng)變多軸等效應(yīng)變疲勞壽命預(yù)測(cè)方法等方法進(jìn)行了對(duì)比分析,建立起基于Von Mises屈服理論的葉輪構(gòu)件的多軸等效應(yīng)變疲勞壽命預(yù)測(cè)模型。研究了葉輪再制造構(gòu)件的疲勞失效機(jī)理并建立了葉輪再制造構(gòu)件的壽命預(yù)測(cè)模型。以葉輪疲勞失效為葉輪再制造的主要研究方向,以激光熔覆技術(shù)作為葉輪再制造的關(guān)鍵技術(shù)對(duì)葉輪進(jìn)行修復(fù),通過參數(shù)優(yōu)化確定最優(yōu)激光熔覆工藝,基于綜合試驗(yàn)平臺(tái)和再制造葉輪構(gòu)件,對(duì)模擬工況下的再制造葉輪構(gòu)件失效性形式和機(jī)理進(jìn)行了分類和表征,并對(duì)修正的Soderberg曲線預(yù)測(cè)再制造葉輪構(gòu)件疲勞極限準(zhǔn)確性進(jìn)行了驗(yàn)證。以修正的基于Von Mises等效應(yīng)變屈服理論的葉輪多軸疲勞壽命預(yù)測(cè)模型為基礎(chǔ),引入再制造特征修正參數(shù),得到了二次修正后Von Mises屈服理論的多軸等效應(yīng)變疲勞壽命預(yù)測(cè)方法,獲得了再制造葉輪構(gòu)件的壽命預(yù)測(cè)模型。利用與新品葉輪相同的臺(tái)架考核標(biāo)準(zhǔn)對(duì)激光再制造葉輪進(jìn)行了強(qiáng)度考核,經(jīng)傳統(tǒng)無(wú)損檢測(cè)方法和工業(yè)CT對(duì)考核后的葉輪進(jìn)行檢測(cè)和表征,未發(fā)現(xiàn)葉輪表面和內(nèi)部有宏觀和微觀缺陷,再制造特征葉輪強(qiáng)度滿足裝機(jī)要求。
[Abstract]:Large compressor belongs to the major equipment machinery. It is widely used in the national economic pillar industries, such as metallurgy, chemical industry and electric power. It is one of the landmark equipment to measure the industrial development level of a country. The compressor rotor is composed of two parts of the spindle and the impeller. It is the key component to ensure the stable operation of the compressor unit. The core problem of remanufacturing development in China is the shortage of remanufacturing basic research. It is necessary to solve the fatigue failure mechanism of the remanufacturing object, the life evolution law and the life prediction, and so on. This subject takes the rotor of high added value as the research object, and studies the fatigue failure of the rotor spindle and the impeller system. The mechanism of the remanufacturing life prediction model is of great significance to the research of rich rotor fatigue foundation and the industrialization of remanufacturing industry. The research on the fatigue damage mechanism and life evolution law of the rotor in the service process is the prerequisite and foundation for the remanufacturing of the rotor. It is difficult to quantify the change of the internal strain of the rotor in the actual working condition, and then analyze the fatigue failure mechanism and the law of life evolution. In this paper, the finite element method is used to simplify the rotor's geometry, boundary conditions and load conditions, and the rotor spindle is modeled and meshed by precise modeling and mesh division. The stress and strain distribution in the spindle under rolling contact is analyzed, the fatigue damage mechanism of the spindle is determined, and the effect of abnormal synergy on the fatigue damage and life evolution of the impeller is analyzed, and the process load and the extreme work are also analyzed. The effect of the load on the life of the rotor is discussed and studied. These studies provide the theoretical basis for remanufacturing the impeller. The main research direction is the contact fatigue failure of the spindle. Based on the high efficiency and low cost of the plasma spraying technology, the key to the spindle in the rotor is the supersonic plasma spraying. The optimal process parameters are determined by orthogonal method. The high quality main shaft remanufacturing coating is obtained by supersonic plasma spraying. The fatigue damage specimen morphology is obtained by the new rolling contact fatigue test machine in the project group. The different failure morphology is characterized by SEM, and the statistical method of large sample is used. The failure mode of the coating is classified, and the contact fatigue failure mechanism of the coating under the different contact stress level is systematically studied. The contact fatigue life model of the spindle remanufacture is established through the P-S-N curve. The mechanical and structural similarity of the dangerous structure parts of the impeller is simplified and simplified to determine the complex size and structure characteristics of the impeller. The form and size of the specimen, which can represent the dangerous structure of the impeller, are developed and built on the basis of the size and form of the specimen. The fatigue failure mechanism of the impeller components is studied and the life prediction model of the impeller components is established. The failure modes and mechanisms of the impeller components under simulated working conditions are classified and characterized, and the Soderberg curves for predicting the fatigue limit of the impeller components are modified and tested. Based on the multi axis fatigue model, the empirical and semi empirical formula method for multi axis fatigue life prediction, based on the maximum principal strain of the multi axis effect, is made. The fatigue life prediction method is compared and analyzed based on the equivalent strain multi axis equivalent effect variable fatigue life prediction method and the maximum shear strain multi axis equal effect variable fatigue life prediction method. The multi axle equivalent effect fatigue life prediction model of the impeller components based on the Von Mises yield theory is established. The fatigue failure mechanism of the remanufactured component and the life prediction model of the remanufactured component of the impeller are established. The main research direction of the impeller remanufacture is the fatigue failure of the impeller. The laser cladding technology is used as the key technology for the remanufacturing of the impeller to repair the impeller, and the optimum laser cladding process is determined by the optimization of the parameters, based on the comprehensive test. The test platform and remanufactured impeller component are classified and characterized for the failure form and mechanism of remanufacturing impeller members under simulated working conditions, and the fatigue limit accuracy of the remanufactured impeller components is verified by the modified Soderberg curve. The modified multiaxial fatigue life of the impeller based on the Von Mises and other effect yield theory is modified. Based on the prediction model and introducing the remanufacturing feature correction parameters, the multi axis equivalent effect fatigue life prediction method of the Von Mises yield theory after two revisions is obtained. The life prediction model of the remanufactured impeller component is obtained. The strength assessment of the laser remanufacturing impeller is carried out by using the same bench test standard as the new impeller. The non destructive testing method and industrial CT are used to detect and characterize the impellers after examination. There are no macroscopic and microscopic defects on the surface and interior of the impeller, and the strength of the characteristic impeller meets the requirements of the loading.
【學(xué)位授予單位】：燕山大學(xué)
【學(xué)位級(jí)別】：博士
【學(xué)位授予年份】：2016
【分類號(hào)】：TH45

【相似文獻(xiàn)】

相關(guān)期刊論文 前10條

1 曲明哲;;橡膠壽命預(yù)測(cè)研究方法[J];科技創(chuàng)新與應(yīng)用;2012年21期

2 李耀君;;鍋爐管的球化評(píng)定與壽命預(yù)測(cè)[J];熱力發(fā)電;1992年06期

3 呂文元;;重大設(shè)備壽命預(yù)測(cè)的技術(shù)和方法[J];中國(guó)設(shè)備工程;2011年03期

4 張小麗;陳雪峰;李兵;何正嘉;;機(jī)械重大裝備壽命預(yù)測(cè)綜述[J];機(jī)械工程學(xué)報(bào);2011年11期

5 蘇翰生;;改裝的蠕變-疲勞試驗(yàn)設(shè)備及其壽命預(yù)測(cè)[J];試驗(yàn)技術(shù)與試驗(yàn)機(jī);1990年03期

6 蘇翰生;;高溫合金循環(huán)蠕變及其壽命預(yù)測(cè)[J];航空材料;1991年02期

7 劉湘生;局部應(yīng)力應(yīng)變法壽命預(yù)測(cè)應(yīng)用研究[J];航空動(dòng)力學(xué)報(bào);1992年02期

8 黃仁聰;;機(jī)械重大裝備壽命預(yù)測(cè)綜述[J];科技致富向?qū)?2013年21期

9 劉婷;張鐸;周源泉;孫頡;;產(chǎn)品壽命預(yù)測(cè)[J];強(qiáng)度與環(huán)境;2007年04期

10 何世禹;;航天器在軌壽命預(yù)測(cè)與可靠性評(píng)價(jià)[J];航天器環(huán)境工程;2008年03期

相關(guān)會(huì)議論文 前10條

1 涂善東;;重大裝備的壽命預(yù)測(cè)與監(jiān)測(cè)技術(shù)[A];壓力容器先進(jìn)技術(shù)——第七屆全國(guó)壓力容器學(xué)術(shù)會(huì)議論文集[C];2009年

2 尚德廣;王大康;姚衛(wèi)星;;隨機(jī)疲勞壽命預(yù)測(cè)的場(chǎng)強(qiáng)法研究[A];疲勞與斷裂2000——第十屆全國(guó)疲勞與斷裂學(xué)術(shù)會(huì)議論文集[C];2000年

3 周昌玉;涂善東;;高溫構(gòu)件壽命預(yù)測(cè)技術(shù)研究進(jìn)展[A];第五屆全國(guó)壓力容器學(xué)術(shù)會(huì)議論文集[C];2001年

4 宋麗;盧曦;郁望達(dá);李玉鵬;朱寧;;考慮強(qiáng)化效應(yīng)的動(dòng)態(tài)S-N曲線壽命預(yù)測(cè)研究[A];第十五屆全國(guó)疲勞與斷裂學(xué)術(shù)會(huì)議摘要及論文集[C];2010年

5 吳學(xué)仁;劉建中;;基于小裂紋理論的航空材料疲勞全壽命預(yù)測(cè)[A];首屆全國(guó)航空航天領(lǐng)域中的力學(xué)問題學(xué)術(shù)研討會(huì)論文集（下冊(cè)）[C];2004年

6 劉虹;張岐山;;改進(jìn)PSO-GM(1,1)及其在產(chǎn)品壽命預(yù)測(cè)中的應(yīng)用[A];第19屆灰色系統(tǒng)全國(guó)會(huì)議論文集[C];2010年

7 錢桂安;王茂廷;王蓮;;用局部應(yīng)力應(yīng)變法進(jìn)行高周疲勞壽命預(yù)測(cè)的研究[A];第十二屆全國(guó)疲勞與斷裂學(xué)術(shù)會(huì)議論文集[C];2004年

8 康嘉杰;徐濱士;王海斗;王成彪;;基于電學(xué)方法的再制造零部件缺陷檢測(cè)與壽命預(yù)測(cè)應(yīng)用基礎(chǔ)研究[A];2011年全國(guó)青年摩擦學(xué)與表面工程學(xué)術(shù)會(huì)議論文集[C];2011年

9 孫麗;汪清海;王世光;張_g;;氯鹽環(huán)境下混凝土的壽命預(yù)測(cè)研究[A];第十一屆沈陽(yáng)科學(xué)學(xué)術(shù)年會(huì)暨中國(guó)汽車產(chǎn)業(yè)集聚區(qū)發(fā)展與合作論壇論文集（信息科學(xué)與工程技術(shù)分冊(cè)）[C];2014年

10 李東哲;劉冬歡;尚新春;;航空發(fā)動(dòng)機(jī)渦輪葉片的蠕變損傷數(shù)值仿真及壽命預(yù)測(cè)[A];北京力學(xué)會(huì)第20屆學(xué)術(shù)年會(huì)論文集[C];2014年

相關(guān)博士學(xué)位論文 前6條

1 楊碩;渦扇發(fā)動(dòng)機(jī)高壓壓氣機(jī)葉片裂紋萌生及擴(kuò)展壽命預(yù)測(cè)研究[D];天津大學(xué);2015年

2 周京;大型壓縮機(jī)轉(zhuǎn)子疲勞損傷機(jī)理及再制造壽命預(yù)測(cè)基礎(chǔ)研究[D];燕山大學(xué);2016年

3 王瑞杰;基于動(dòng)態(tài)響應(yīng)分析的點(diǎn)焊接頭疲勞損傷與壽命預(yù)測(cè)[D];北京工業(yè)大學(xué);2008年

4 閆明;蠕變—熱疲勞可靠壽命預(yù)測(cè)的若干問題研究[D];東北大學(xué);2008年

5 杜鵬;多因素耦合作用下混凝土的凍融損傷模型與壽命預(yù)測(cè)[D];中國(guó)建筑材料科學(xué)研究總院;2014年

6 欒新剛;3D C/SiC在復(fù)雜耦合環(huán)境中的損傷機(jī)理與壽命預(yù)測(cè)[D];西北工業(yè)大學(xué);2007年

相關(guān)碩士學(xué)位論文 前10條

1 馬苓;兩種鋰原電池高溫儲(chǔ)存性能研究及壽命預(yù)測(cè)[D];天津大學(xué);2014年

2 許爾威;材料老化壽命預(yù)測(cè)與軟件開發(fā)[D];東北大學(xué);2014年

3 郭佳歡;車輪彎曲疲勞與徑向疲勞研究及壽命預(yù)測(cè)[D];江蘇大學(xué);2016年

4 蔣鳴遠(yuǎn);基于數(shù)據(jù)管理的測(cè)試性建模與壽命預(yù)測(cè)軟件設(shè)計(jì)與實(shí)現(xiàn)[D];電子科技大學(xué);2016年

5 王立峰;北京市在役地下熱力結(jié)構(gòu)的可靠性評(píng)估及壽命預(yù)測(cè)[D];北京交通大學(xué);2016年

6 王展飛;復(fù)合鹽溶液作用下混凝土耐久性研究與壽命預(yù)測(cè)[D];揚(yáng)州大學(xué);2016年

7 陳健飛;基于SVM的典型機(jī)械聯(lián)接結(jié)構(gòu)壽命預(yù)測(cè)研究[D];西南科技大學(xué);2016年

8 丁瑞;基于信息融合的衛(wèi)星設(shè)備壽命預(yù)測(cè)研究[D];南京航空航天大學(xué);2016年

9 范永斌;某型越野車折疊式軟頂?shù)膭?dòng)力學(xué)分析與壽命預(yù)測(cè)[D];南京航空航天大學(xué);2016年

10 高斯博;基于退化數(shù)據(jù)的壽命預(yù)測(cè)中估計(jì)問題研究[D];大連理工大學(xué);2016年

，

本文編號(hào)：2042130