透平持環(huán)高溫蠕變和結(jié)構(gòu)關(guān)系分析
發(fā)布時間：2019-04-24 02:31
【摘要】：透平部件是燃氣輪機中承受溫度最高的部件之一,透平靜葉持環(huán)是透平部分中最大的鑄鋼件,是燃氣輪機中溫度最高,熱負荷最大的大部件之一。透平靜葉持環(huán)在熱通道檢修和大修中無法使用新部件替換,因此,透平靜葉持環(huán)的使用壽命就決定整臺燃氣輪機壽命的重要因素之一,這關(guān)乎到整臺燃氣輪機的可靠性,因此分析透平靜葉持環(huán)的應(yīng)力、高溫蠕變對部件的安全運行有著重要意義。本文主要研究內(nèi)容如下:1)確定高溫蠕變分析的邊界條件首先分析冷卻通道結(jié)構(gòu),對冷卻流量的分配進行探索和計算,得到了冷卻流量分配的基本原理和各級的分配量,并建立了計算模型;在此基礎(chǔ)上,采用相近結(jié)構(gòu)的對流換熱系數(shù)的計算方法,計算得到了燃氣輪機的持環(huán)各表面的換熱系數(shù);2)透平持環(huán)計算模型的建立與簡化評估透平持環(huán)中冷卻空氣通道等結(jié)構(gòu)對持環(huán)體的高溫蠕變性能影響,在保證計算結(jié)果具有一定準確度的基礎(chǔ)上,簡化計算模型,并完成二維、三維建模。3)透平持環(huán)溫度場、應(yīng)力場計算分析以1)和2)的工作為基礎(chǔ),利用ANSYS計算軟件,計算得到了包含持環(huán)內(nèi)導熱、對流換熱和輻射換熱等物理過程的溫度場和應(yīng)力場分布情況,得到透平持環(huán)的應(yīng)力集中區(qū)域分布在前后的兩個葉根槽處,最大應(yīng)力在前葉根槽處,其初始應(yīng)力最大值為125MPa;4)透平持環(huán)蠕變計算分析通過十萬小時的蠕變仿真計算,發(fā)現(xiàn)模型的應(yīng)力場發(fā)生了改變。在最初的1萬小時,應(yīng)力就降低至原來的50%以下,其最大應(yīng)力點從前葉根槽處轉(zhuǎn)移到了后葉根槽處,最大彈性應(yīng)力值降至61MPa,應(yīng)力松弛速度處于不斷下降的趨勢,至10萬小時后,最大彈性應(yīng)力降至42MPa;蠕變造成前后葉根槽處角度發(fā)生變化,并造成了靜葉片的軸向變形,計算得出靜葉片最大變形分別為1.24mm,均在蠕變允許的范圍之內(nèi)。
[Abstract]:Turbine component is one of the components which bear the highest temperature in gas turbine. Turbine blade holding ring is the largest steel casting in turbine part. It is one of the largest parts in gas turbine with the highest temperature and the largest heat load. It is impossible to replace the new components in hot channel maintenance and overhaul. Therefore, the service life of the turbine is one of the important factors that determine the life of the whole gas turbine, which is related to the reliability of the whole gas turbine. Therefore, it is of great significance for the safe operation of the parts to analyze the stress of the blade holding ring and the creep at high temperature. The main contents of this paper are as follows: 1) to determine the boundary conditions of creep analysis at high temperature, the structure of cooling channel is analyzed firstly, and the distribution of cooling flow rate is explored and calculated, and the basic principle of cooling flow distribution and the distribution quantity of all levels are obtained. The calculation model is established. On the basis of this, the heat transfer coefficient of each surface of the gas turbine holding ring is calculated by using the calculation method of the convection heat transfer coefficient of the similar structure. 2) the establishment and simplification of the calculation model of turbine holding ring and the simplified evaluation of the influence of the structure such as the cooling air passage in the turbine holding ring on the creep behavior of the holding ring at high temperature. On the basis of ensuring the accuracy of the calculation results, the calculation model is simplified. 3) based on the work of 1) and 2), the heat conduction in the holding ring has been calculated by using ANSYS software, and the heat conduction in the holding ring has been calculated. The distribution of temperature field and stress field in the physical process, such as convection heat transfer and radiation heat transfer, is obtained. The stress concentration region of the turbine holding ring is distributed in the two root grooves in front and back, and the maximum stress is in the front root trough, and the maximum initial stress is 125 MPA. 4) through the creep simulation calculation of 100, 000 hours, it is found that the stress field of the model has been changed. In the first 10,000 hours, the stress was reduced to less than 50%, the maximum stress point was transferred from the root groove of the front leaf to the root trough of the posterior lobe, the maximum elastic stress value decreased to 61 MPA, and the stress relaxation rate was in a decreasing trend. After 100000 hours, the maximum elastic stress decreased to 42 MPA; After creep, the angle of the root groove is changed, and the axial deformation of the static blade is caused. The maximum deformation of the blade is 1.24 mm, which is within the allowable range of creep.
【學位授予單位】：上海交通大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：TK473
本文編號：2464031
[Abstract]:Turbine component is one of the components which bear the highest temperature in gas turbine. Turbine blade holding ring is the largest steel casting in turbine part. It is one of the largest parts in gas turbine with the highest temperature and the largest heat load. It is impossible to replace the new components in hot channel maintenance and overhaul. Therefore, the service life of the turbine is one of the important factors that determine the life of the whole gas turbine, which is related to the reliability of the whole gas turbine. Therefore, it is of great significance for the safe operation of the parts to analyze the stress of the blade holding ring and the creep at high temperature. The main contents of this paper are as follows: 1) to determine the boundary conditions of creep analysis at high temperature, the structure of cooling channel is analyzed firstly, and the distribution of cooling flow rate is explored and calculated, and the basic principle of cooling flow distribution and the distribution quantity of all levels are obtained. The calculation model is established. On the basis of this, the heat transfer coefficient of each surface of the gas turbine holding ring is calculated by using the calculation method of the convection heat transfer coefficient of the similar structure. 2) the establishment and simplification of the calculation model of turbine holding ring and the simplified evaluation of the influence of the structure such as the cooling air passage in the turbine holding ring on the creep behavior of the holding ring at high temperature. On the basis of ensuring the accuracy of the calculation results, the calculation model is simplified. 3) based on the work of 1) and 2), the heat conduction in the holding ring has been calculated by using ANSYS software, and the heat conduction in the holding ring has been calculated. The distribution of temperature field and stress field in the physical process, such as convection heat transfer and radiation heat transfer, is obtained. The stress concentration region of the turbine holding ring is distributed in the two root grooves in front and back, and the maximum stress is in the front root trough, and the maximum initial stress is 125 MPA. 4) through the creep simulation calculation of 100, 000 hours, it is found that the stress field of the model has been changed. In the first 10,000 hours, the stress was reduced to less than 50%, the maximum stress point was transferred from the root groove of the front leaf to the root trough of the posterior lobe, the maximum elastic stress value decreased to 61 MPA, and the stress relaxation rate was in a decreasing trend. After 100000 hours, the maximum elastic stress decreased to 42 MPA; After creep, the angle of the root groove is changed, and the axial deformation of the static blade is caused. The maximum deformation of the blade is 1.24 mm, which is within the allowable range of creep.
【學位授予單位】：上海交通大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：TK473
【參考文獻】
相關(guān)期刊論文 前6條
1 林鐵;;GE-9FA燃氣輪機透平葉片冷卻技術(shù)分析[J];機械工程師;2013年08期
2 王輔方;王彬;何磊;崔耀欣;徐強;;透平冷卻空氣量計算方法綜述[J];熱力透平;2011年03期
3 李政;王德慧;倪維斗;;考慮冷卻空氣影響的大型燃氣輪機性能計算模型[J];動力工程;2006年02期
4 王德慧,李政,麻林巍,倪維斗;大型燃氣輪機冷卻空氣量分配及透平膨脹功計算方法研究[J];中國電機工程學報;2004年01期
5 李政,江寧,麻林巍,王德惠,倪維斗;西門子公司V94.3燃氣輪機冷卻空氣信息推測[J];燃氣輪機技術(shù);2002年04期
6 過康民;汽輪機葉片的材料[J];動力工程;1983年04期
，本文編號：2464031
本文鏈接：http://sikaile.net/kejilunwen/dongligc/2464031.html
最近更新
教材專著
