本文選題：燃?xì)廨啓C(jī)　切入點(diǎn)：空氣系統(tǒng)　出處：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：隨著燃?xì)廨啓C(jī)技術(shù)的發(fā)展,渦輪前溫度的上升與渦輪葉片耐高溫材料的限制導(dǎo)致了空氣系統(tǒng)引氣量的提高,空氣系統(tǒng)對(duì)燃?xì)廨啓C(jī)的總體性能的影響越來(lái)越大,因此,對(duì)燃?xì)廨啓C(jī)總體與空氣系統(tǒng)耦合計(jì)算方法研究具有重要價(jià)值。本文結(jié)合前人研究成果以及工程氣動(dòng)熱力理論,對(duì)燃?xì)廨啓C(jī)總體性能仿真方法與空氣系統(tǒng)可壓縮流體網(wǎng)絡(luò)建模方法分別進(jìn)行了研究,并在此基礎(chǔ)上對(duì)考慮空氣系統(tǒng)影響的燃?xì)廨啓C(jī)總體性能進(jìn)行了匹配分析�；跓崃W(xué)原理對(duì)燃?xì)廨啓C(jī)熱力計(jì)算方法進(jìn)行了研究,確定了變比熱計(jì)算工質(zhì)物性參數(shù)、等溫焓差法確定燃燒室油氣比的方法。通過(guò)這些方法,建立了燃?xì)廨啓C(jī)各部件包括進(jìn)氣道、壓氣機(jī)、燃燒室、渦輪、噴管的熱力性能計(jì)算模型,完成了燃?xì)廨啓C(jī)從進(jìn)口到出口各個(gè)截面氣動(dòng)熱力參數(shù)的計(jì)算鏈。在燃?xì)廨啓C(jī)共同工作條件的基礎(chǔ)上,確定了Newton-Raphson迭代求解的匹配計(jì)算思路,其中對(duì)于轉(zhuǎn)子部件特性曲線的處理,采用非對(duì)齊數(shù)據(jù)二元插值法提取壓氣機(jī)渦輪性能的方法。同時(shí)針對(duì)航空發(fā)動(dòng)機(jī)空氣系統(tǒng)中高速氣體流動(dòng)計(jì)算,采用流體網(wǎng)絡(luò)法進(jìn)行節(jié)點(diǎn)分支網(wǎng)絡(luò)建模。其中采用了廣義一維流動(dòng)理論,通過(guò)比擬變換和龍格—庫(kù)塔數(shù)值積分方法求解微分方程,得到簡(jiǎn)單分支結(jié)構(gòu)(漸變截面換熱管流動(dòng))流動(dòng)參數(shù)的求解方法;采用經(jīng)驗(yàn)損失系數(shù)方法求解復(fù)雜分支結(jié)構(gòu)(截面突變、彎管、帶網(wǎng)格截面、三通管)的進(jìn)出口流動(dòng)參數(shù)關(guān)系,最終形成一套適用于空氣系統(tǒng)以及類似的氣路管網(wǎng)計(jì)算建模方法。根據(jù)上述研究的熱力計(jì)算建模方法,在考慮空氣系統(tǒng)從高低壓氣機(jī)引氣冷卻渦輪葉片對(duì)燃?xì)廨啓C(jī)總體性能的影響的基礎(chǔ)上,開(kāi)發(fā)了燃?xì)廨啓C(jī)總體和空氣系統(tǒng)耦合計(jì)算工具。針對(duì)某型地面航改燃?xì)廨啓C(jī),計(jì)算并分析了不同工作環(huán)境、不同油門(mén)角度、不同動(dòng)力渦輪導(dǎo)向器安裝角下燃?xì)廨啓C(jī)總體性能變化規(guī)律。并且,特別針對(duì)空氣系統(tǒng)影響,在控制尾噴管面積以及動(dòng)力渦輪轉(zhuǎn)速的情況下,得到如下結(jié)論:保持油門(mén)角度不變,隨著引氣量的提高,渦輪前溫度隨之提高,總功率相應(yīng)的提高了,耗油率先增加后降低;保持油門(mén)角度可調(diào),使引氣量隨著渦輪前溫度增大相應(yīng)增大,則輸出功率提高,耗油率先降低后提高,存在最佳耗油率。
[Abstract]:With the development of gas turbine technology, the increase of turbine front temperature and the limitation of high temperature resistant material of turbine blade lead to the increase of air entrainment, and the influence of air system on the overall performance of gas turbine is more and more great.It is of great value to study the coupling calculation method between gas turbine and air system.In this paper, combined with previous research results and engineering aerodynamics theory, the simulation method of gas turbine's overall performance and the modeling method of compressible fluid network for air system are studied respectively.On this basis, the overall performance of gas turbine considering the influence of air system is analyzed.Based on the thermodynamic principle, the thermodynamic calculation method of gas turbine is studied, and the calculation parameters of working fluid properties with variable specific heat and the method of determining the oil / gas ratio of combustion chamber by isothermal enthalpy difference method are determined.Through these methods, the thermodynamic performance calculation model of gas turbine components including inlet, compressor, combustion chamber, turbine and nozzle is established, and the calculation chain of aerodynamic thermodynamic parameters of each section of gas turbine from inlet to outlet is completed.On the basis of the common working conditions of gas turbines, the matching calculation idea of Newton-Raphson iterative solution is determined, in which the non-aligned data binary interpolation method is used to extract compressor turbine performance for the processing of rotor component characteristic curves.At the same time, the node branch network is modeled by using fluid network method to calculate the high speed gas flow in the aero-engine air system.The generalized one-dimensional flow theory is used to solve the differential equations by analogy transformation and Runge-Kutta numerical integral method.The empirical loss coefficient method is used to solve the inlet and outlet flow parameter relations of complex branch structures (section mutation, curved pipe, gridding section, three-way pipe). Finally, a set of modeling method for air system and similar gas pipeline network is developed.On the basis of the thermodynamic calculation modeling method mentioned above and considering the effect of the turbine blade on the overall performance of the gas turbine, a coupling calculation tool between the gas turbine and the air system is developed.The general performance of gas turbine under different working environment, different throttle angle and different installation angle of power turbine guide is calculated and analyzed for a certain type of ground aeronautical modified gas turbine.Especially for the influence of air system, under the condition of controlling the area of nozzle and the speed of power turbine, the conclusion is as follows: keeping the angle of throttle constant, the temperature of turbine front increases with the increase of entrainment.With the increase of the total power, the oil consumption increases first and then decreases, and the angle of throttle is adjustable, so that the gas intake increases with the increase of turbine temperature, the output power increases and the oil consumption decreases first and then increases, and there is the best fuel consumption rate.
【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)】：TK472

【參考文獻(xiàn)】

相關(guān)期刊論文 前10條

1 顧華年;朱志R，

本文編號(hào)：1715023