【摘要】：發(fā)動機機匣設(shè)計中,主要依靠恰當?shù)臋C匣結(jié)構(gòu)和冷卻流路設(shè)計來控制轉(zhuǎn)子部件和機匣的徑向位移,從而達到控制葉尖間隙的目的。機匣典型結(jié)構(gòu)的優(yōu)化設(shè)計是機匣結(jié)構(gòu)設(shè)計中必不可少的一環(huán)。本文針對高壓渦輪機匣軸對稱模型熱固耦合單目標以及多目標優(yōu)化設(shè)計方法進行了研究,主包括以下三個方面的內(nèi)容:(1)采用實驗技術(shù)對高壓渦輪機匣熱固耦合分析方法進行驗證,搭建相應(yīng)試驗臺,獲得模擬機匣熱變形以及溫度分布。針對實驗工況下的模擬機匣進行熱固耦合有限元分析,并對試驗實測變形量和仿真變形量進行對比,結(jié)果表明:文中高壓渦輪機匣熱固耦合分析方法得到的溫度及熱變形精度基本符合工程應(yīng)用要求。(2)建立基于UG表達式文件EXP驅(qū)動的高壓渦輪機匣軸對稱參數(shù)化模型,針對高壓渦輪機匣軸對稱參數(shù)化模型進行了熱固耦合有限元分析,并對結(jié)構(gòu)參數(shù)進行了靈敏度分析,基于靈敏度分析結(jié)果開展了高壓渦輪機匣軸對稱模型熱固耦合單目標及多目標優(yōu)化設(shè)計,優(yōu)化結(jié)果表明:經(jīng)過單目標優(yōu)化之后,掛鉤處徑向平均位移值減小9.85%;經(jīng)過多目標優(yōu)化后機匣等效質(zhì)量減輕4.54%,掛鉤處徑向平均位移值減小8.90%;跟單目標優(yōu)化設(shè)計法相比,多目標優(yōu)化設(shè)計更符合航空發(fā)動機設(shè)計需要。(3)采用響應(yīng)面模型、人工神經(jīng)網(wǎng)絡(luò)模型以及Kriging模型構(gòu)建了高壓渦輪機匣熱固耦合優(yōu)化近似模型,對近似模型設(shè)置參數(shù)與預(yù)測精度之間關(guān)系進行研究,并利用近似模型對高壓渦輪機匣模型進行了近似優(yōu)化,結(jié)果表明:應(yīng)用的三種近似模型均能夠達到實際模型的優(yōu)化效果,單目標優(yōu)化選擇基于徑向基函數(shù)的人工神經(jīng)網(wǎng)絡(luò)模型(RBF),多目標優(yōu)化選擇總誤差最小的響應(yīng)面模型(RSM)。
[Abstract]:In the design of engine casing, the radial displacement of rotor parts and casing is mainly controlled by proper casing structure and cooling flow path design, so as to control the tip clearance. The optimal design of the typical casing structure is an indispensable part of the casing structure design. In this paper, the optimization design method of thermo-solid coupling and multi-objective optimization for axisymmetric model of high-pressure turbine casing is studied. The main contents include the following three aspects: (1) the thermal-solid coupling analysis method of high-pressure turbine casing is verified by experimental technology, and the corresponding test bench is built to obtain the simulation of heat deformation and temperature distribution of the casing. The thermo-solid coupling finite element analysis is carried out for the simulated casing under experimental conditions, and a comparison between the measured deformation and the simulated deformation is carried out. The results show that the temperature and thermal deformation accuracy obtained by the thermal-solid coupling analysis method of high pressure turbine casing basically meet the requirements of engineering application. (2) the axisymmetric parameterized model of high pressure turbine casing driven by UG expression file exp is established. Based on the axisymmetric parameterized model of high pressure turbine casing, the thermo-solid coupling finite element analysis is carried out, and the sensitivity analysis of structural parameters is carried out. Based on the sensitivity analysis results, the thermo-solid coupled single-objective and multi-objective optimization design of the axisymmetric model of high-pressure turbine casing is carried out. The optimization results show that: after single-objective optimization, After multi-objective optimization, the equivalent mass of the casing is reduced by 4.54 and the radial average displacement at the hook is reduced by 8.90. Compared with the single objective optimization design method, Multi-objective optimization design is more in line with the need of aeroengine design. (3) using response surface model, artificial neural network model and Kriging model, the thermo-solid coupling optimization approximation model of high-pressure turbine casing is constructed. The relationship between the parameters of the approximate model and the prediction accuracy is studied, and the high pressure turbine casing model is approximately optimized by using the approximate model. The results show that the three kinds of approximate models can achieve the optimization effect of the actual model. The radial basis function based artificial neural network model (RBF) and the response surface model (RSM) with minimum total error are selected for single objective optimization.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V231.1

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