【摘要】：葉輪機械葉片設(shè)計中通常采用的方法有正問題設(shè)計方法和反問題設(shè)計方法。正問題設(shè)計中設(shè)計人員通過分析設(shè)計要求，選擇性能相近的葉型作為初始葉型，通過CFD或試驗方法分析初始葉型氣動性能，如果其不滿足設(shè)計要求，，則根據(jù)相關(guān)經(jīng)驗或給定的優(yōu)化準(zhǔn)則反復(fù)修改葉型，直到其達到要求。正問題方法具有過程簡單、易于實現(xiàn)等優(yōu)點，但設(shè)計過程要耗費大量時間和成本。反問題設(shè)計中，設(shè)計人員根據(jù)設(shè)計要求給出流場中某些氣動參數(shù)，通過氣動參數(shù)與幾何造型間的物理關(guān)系得到實現(xiàn)該流動特征的葉型。因此反問題設(shè)計的優(yōu)勢在于設(shè)計效率較高、對設(shè)計人員經(jīng)驗依賴較少。本文在馮卡門流體研究所（VKI）相關(guān)研究的基礎(chǔ)上開展了葉片反問題設(shè)計方法的研究。全文研究內(nèi)容主要包括以下幾個方面： （1）構(gòu)建了葉型無粘反問題設(shè)計流程，對其中的關(guān)鍵技術(shù)——基于特征變量邊界理論的滲透邊界、葉型修正技術(shù)進行了原理分析，并在課題組自主開發(fā)的計算流體力學(xué)軟件NAPA中完成了滲透邊界、葉型修正模塊等無粘反問題設(shè)計組成部分的程序?qū)崿F(xiàn)，從而實現(xiàn)了葉型反問題設(shè)計。 （2）對以下3類9個具有不同流動特點的管道及葉柵算例進行了反問題設(shè)計：1）無轉(zhuǎn)折的曲壁面通道，如bump管道，二維拉瓦爾噴管；2）模擬單葉柵通道流動的轉(zhuǎn)彎擴張通道；3）雙圓弧葉型構(gòu)成的平面葉柵。分別在氣流無轉(zhuǎn)折及氣流發(fā)生轉(zhuǎn)折的亞聲速流動、存在激波的跨聲速流動中逐步驗證該無粘反問題設(shè)計方法的準(zhǔn)確性。 （3）針對反問題設(shè)計方法實際使用時可能出現(xiàn)的目標(biāo)流動與初始流動的流場結(jié)構(gòu)間存在較大差異的情況，改進了滲透邊界的處理方法，并在消除葉柵流動中槽道激波的反問題設(shè)計算例中進行了驗證。 （4）把無粘反問題設(shè)計方法推廣到粘性流動中，構(gòu)建了葉型粘性反問題設(shè)計流程。在雙圓弧葉型的亞聲速流動中進行了粘性反問題設(shè)計的驗證。改進了粘性反問題設(shè)計過程中無粘目標(biāo)壓力分布的預(yù)估方法，使之適用于存在激波的流動，并在存在激波的葉柵流動中進行了驗證。 （5）針對NASALewis研究中心設(shè)計的一款兩級風(fēng)扇的第二級轉(zhuǎn)子葉片葉中截面的葉型，應(yīng)用本文構(gòu)建的反問題設(shè)計技術(shù)進行了改進設(shè)計。改進后的葉型，在進口流動條件一致，保證葉型載荷不減小的前提下，流動損失減小。計算表明在來流馬赫數(shù)1.02時，改進后的葉型其載荷較初始葉型提高2.2%，靜壓升系數(shù)提高9.4%，總壓損失減小1.47%。
[Abstract]:The methods used in blade design of impeller machinery include forward problem design method and inverse problem design method. In the forward problem design, the designers choose the blade shape with similar performance as the initial blade shape by analyzing the design requirements, and analyze the aerodynamic performance of the initial blade shape by CFD or test method, if it does not meet the design requirements, The leaf profile is modified repeatedly according to relevant experience or given optimization criteria until it meets the requirements. The forward problem method has the advantages of simple process and easy implementation, but the design process needs a lot of time and cost. In inverse problem design, some aerodynamic parameters in the flow field are given according to the design requirements, and the blade profile of the flow characteristic is obtained by the physical relationship between the aerodynamic parameters and the geometric modeling. Therefore, the advantage of inverse problem design lies in its high design efficiency and less dependence on the designer's experience. In this paper, the design method of blade inverse problem is studied on the basis of the (VKI) research of von Carmen fluid Research Institute. The main contents of this paper are as follows: (1) the design process of blade inviscid inverse problem is constructed, and the infiltration boundary based on characteristic variable boundary theory is discussed. The principle of blade shape correction technology is analyzed, and the program of non-viscous inverse problem design, such as seepage boundary and blade shape correction module, is implemented in the computational fluid dynamics software NAPA, which is developed by the research group. Thus, the design of blade shape inverse problem is realized. (2) for the following three types of pipes and cascades with different flow characteristics, inverse problem design: 1) curved wall channel without turning, such as bump pipe, two-dimensional Laval nozzle, 2) turn expansion channel simulating flow in single cascade channel; 3) a planar cascade with double arc blades. The accuracy of the design method is verified step by step in the transonic flow with shock wave and the subsonic flow with no turning or turning of the flow. (3) in view of the large difference between the structure of the target flow and the flow field of the initial flow when the inverse problem design method is used in practice, the method of dealing with the permeation boundary is improved. The design example of the inverse problem of eliminating the channel shock in cascade flow is verified. (4) the inviscid inverse problem design method is extended to viscous flow, and the design flow of blade viscous inverse problem is constructed. The design of viscous inverse problem is verified in subsonic flow with double arc blades. The method of predicting the pressure distribution of non-viscous target in the design process of viscous inverse problem is improved to make it suitable for the flow with shock wave, and it is verified in the cascade flow with shock wave. (5) aiming at the blade profile of the second stage rotor blade of a two-stage fan designed by NASALewis Research Center, the inverse problem design technique constructed in this paper is used to improve the design. The flow loss of the improved blade is reduced on the premise that the inlet flow condition is the same and the load of the blade shape is not reduced. The calculation results show that the load of the improved blade shape is increased by 2.2 than that of the initial blade shape, the static pressure rising coefficient is increased by 9.4and the total pressure loss is reduced by 1.47m when the Mach number is 1.02.
【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】：2012
【分類號】：TH45

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