本文關(guān)鍵詞： 葉尖徑向間隙 有限元模型 渦流密度 數(shù)值仿真 溫度和離心載荷　出處：《南京航空航天大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

【摘要】：航空發(fā)動(dòng)機(jī)的渦輪葉尖徑向間隙對(duì)發(fā)動(dòng)機(jī)工作效率和安全具有重要影響,本文圍繞渦輪葉尖徑向間隙數(shù)值分析與檢測(cè)技術(shù)中的若干問題開展研究。本文首先開展了渦輪葉尖間隙數(shù)值仿真研究,以某型航空發(fā)動(dòng)機(jī)低壓渦輪為研究對(duì)象,綜合考慮離心載荷和溫度載荷的影響,結(jié)合表征該型發(fā)動(dòng)機(jī)整機(jī)性能的起動(dòng)數(shù)學(xué)模型,提出了在發(fā)動(dòng)機(jī)起動(dòng)的全過程渦輪葉尖徑向間隙有限元仿真方法。仿真結(jié)果表明在發(fā)動(dòng)機(jī)起動(dòng)過程中,機(jī)匣和葉片的徑向變形主要受溫度載荷的影響,輪盤的徑向變形主要受離心載荷影響。綜合對(duì)比數(shù)值分析計(jì)算結(jié)果和該型發(fā)動(dòng)機(jī)手冊(cè)數(shù)據(jù),顯示兩者基本相等,驗(yàn)證了數(shù)值分析結(jié)果的正確性。本文分析了電渦流傳感器的基本原理,根據(jù)電渦流原理和有限元建模理論,建立了電渦流三維有限元模型,獲得了被測(cè)導(dǎo)體中電渦流分布情況;對(duì)比具有不同探頭形狀的傳感器的電渦流分布,設(shè)計(jì)了用于葉尖間隙測(cè)量的傳感器探頭線圈;根據(jù)渦輪葉尖徑向間隙特性和現(xiàn)有傳感器測(cè)量電路,設(shè)計(jì)了新的測(cè)量電路原理圖。利用所設(shè)計(jì)測(cè)量電路和傳感器探頭制作電渦流傳感器,并對(duì)其靜態(tài)特性和動(dòng)態(tài)特性開展實(shí)驗(yàn)研究。對(duì)靜態(tài)標(biāo)定數(shù)據(jù)進(jìn)行最小二乘直線擬合,結(jié)果表明設(shè)計(jì)制作的傳感器在2~11mm的測(cè)量區(qū)間線性度較好,對(duì)靜態(tài)標(biāo)定數(shù)據(jù)進(jìn)行曲線擬合,顯示高斯法擬合曲線與標(biāo)定數(shù)據(jù)吻合度最高。動(dòng)態(tài)測(cè)量實(shí)驗(yàn)中,設(shè)計(jì)了輪齒高低變化的音輪用來模擬葉尖間隙變化,對(duì)傳感器通過單組輪齒進(jìn)行周向標(biāo)定,并在不同轉(zhuǎn)速下測(cè)量葉尖間隙,將所測(cè)數(shù)據(jù)與標(biāo)定數(shù)據(jù)對(duì)比,顯示所設(shè)計(jì)制作傳感器能夠應(yīng)用于測(cè)量葉尖徑向間隙。
[Abstract]:The radial clearance of the turbine tip of an aeroengine has an important effect on the efficiency and safety of the engine. In this paper, some problems in the numerical analysis and detection of radial clearance of turbine tip are studied. Firstly, numerical simulation of tip clearance of turbine blade is carried out, and a low pressure turbine of an aero-engine is taken as an object of study. Considering the influence of centrifugal load and temperature load, combined with the starting mathematical model to characterize the performance of the engine, A finite element simulation method for the radial clearance of turbine blade tip in the whole process of engine starting is presented. The simulation results show that the radial deformation of casing and blade is mainly affected by temperature load during engine starting. The radial deformation of the wheel disk is mainly affected by centrifugal load. Compared with the numerical analysis results and the data of the engine manual, it is shown that the two are basically equal. In this paper, the basic principle of eddy current sensor is analyzed. According to the theory of eddy current and finite element modeling theory, the three-dimensional finite element model of eddy current is established, and the eddy current distribution in measured conductor is obtained. Comparing the eddy current distribution of sensors with different probe shapes, the transducer coil for measuring tip clearance is designed, and according to the radial clearance characteristics of turbine blade tip and the current sensor measuring circuit, A new measuring circuit schematic diagram is designed. The eddy current sensor is fabricated by using the designed measuring circuit and sensor probe. The static and dynamic characteristics of the eddy current sensor are studied experimentally. The static calibration data are fitted by the least square straight line. The results show that the linearity of the sensor designed and manufactured is good at the measuring range of 210mm. The curve fitting of static calibration data shows that the fitting curve of Gao Si method is the best with the calibration data. A sound wheel with varying gear teeth was designed to simulate the change of tip clearance. The sensor was calibrated circumferentially through a single set of gear teeth. The tip clearance was measured at different rotational speeds, and the measured data were compared with the calibrated data. It shows that the sensor can be used to measure radial clearance of blade tip.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V232

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