涡轮叶间超紧凑燃烧室研究

发布时间：2017-12-31 06:17

本文关键词：涡轮叶间超紧凑燃烧室研究　出处：《南京航空航天大学》2016年硕士论文　论文类型：学位论文

【摘要】：涡轮叶间超紧凑燃烧室作为一种新型燃烧室,以其结构紧凑,燃烧效率高,压力损失小的特点应用于燃气涡轮发动机。本文在已有研究的基础之上,设计了涡轮叶间燃烧室的试验件模型(Turbine inter-Blade Burner with 3 Cavities,简称TIB-3C)以及与之配套的试验系统,进行了初步的验证性试验测量,并且利用CFD软件FLUENT对试验件简化模型进行数值模拟,探究流量分配与操作压力对燃烧室性能的影响。此外,本文针对不同结构的主燃(Main Combustor,MC)-涡轮叶间补燃(Turbine inter-Blade Burner,TIB)一体化燃烧室(简称MC-TIB)进行了数值模拟分析,主要研究了燃烧环长宽比以及燃烧环射流角对主燃-涡轮叶间补燃一体化燃烧室性能的影响。本文首先研究了燃烧工况对涡轮叶间超紧凑燃烧室(TIB-3C)的影响,发现:(1)在总流量保持不变的条件下,适当提高二次流流量,有利于提高出口速度,改善出口温度分布,提高燃烧效率,降低出口污染物污染物NOx、CO以及UHC的排放,并且在较高二次流流量工况下,出口径向平均温度分布较理想,有利于燃烧室的设计;(2)适当的增加燃烧室的操作压力有利于总压损失的减少,提高燃烧效率,提高出口温度,减少污染物CO以及UHC的排放。随后,本文对涡轮叶间超紧凑燃烧室TIB-3C模型进行了试验件的设计,并且进行了以验证性为目的的初步试验,试验成果包括:(1)设计了燃烧环射流角度组合45°55、燃烧环长宽比0.6、涡轮导向器采用带凹槽的弯曲叶片、加入了预旋叶片的涡轮叶间超紧凑燃烧室试验件(TIB-3C)模型;(2)设计了针对涡轮叶间超紧凑燃烧室试验件(TIB-3C)的试验系统(3)保持总流量不变,减少主流流量,增加二次流流量,会导致总压损失增大,并且与数值模拟计算的结果对比发现,相对误差在10%左右,二者吻合较好。(4)涡轮导向器叶片温度分布的试验数据与数值模拟相比,相对误差在18%左右,试验得出的结论与数值计算的结果吻合较好。最后,本文对不同结构的主燃-涡轮叶间补燃一体化燃烧室(MC-TIB)燃烧室进行了数值模拟研究,研究表明:(1)MC-TIB的燃烧环长宽比直接影响了补燃室中燃烧反应的空间尺度,对燃烧特性产生直接的影响,提高燃烧环长宽比,有利于提高出口速度,改善出口速度分布,增加出口温度,减少压力损失;降低燃烧环长宽比,有利于强化主次流掺混,改善温度分布,降低污染物NOx以及UHC排放;(2)MC-TIB燃烧室的燃烧环射流角度直接影响燃烧环内流体的流场分布,对燃烧性能造成影响,适当的增大射流角度,有利于提高出口速度,改善速度分布,减少UHC排放;减小射流角度,有利于提高出口温度,改善出口温度分布,降低NOx污染物排放;射流角度的改变对压力损失的影响较小。
[Abstract]:Turbine blade Jianchao compact combustion chamber as a new type of combustion chamber, with its compact structure, high combustion efficiency, low pressure drop characteristics used in gas turbine engines. This paper based on the research, designed a test model of turbine blade between the combustion chamber (3 Turbine inter-Blade Burner with Cavities, referred to as TIB-3C) and with the support of the test system, tests and preliminary measurements, using CFD software FLUENT to test a simplified model for numerical simulation of flow distribution and effect of operating pressure on the combustion performance. In addition, according to the different structure of the main combustion (Main Combustor, MC) - turbine burning between (Turbine inter-Blade Burner, TIB) integrated combustion chamber (MC-TIB) numerical simulation analysis, mainly studies the combustion ring length width ratio and angle of the main jet combustion ring of gas - Turbine inter vane Effect of combustion chamber performance integration combustion. This paper studies the combustion condition of turbine blade Jianchao compact combustion chamber (TIB-3C) effect, found that: (1) remain unchanged in terms of total flow rate, increasing two times flow, is beneficial to improve the export rate, improve the exit temperature distribution, improve combustion efficiency, reduce export of pollutants NOx, CO and UHC emissions, and two times higher in the flow stream, the outlet radial average temperature distribution is ideal and is conducive to the design of the combustion chamber; (2) reduce the proper increase of the operating pressure of combustion chamber to the total pressure loss, improve combustion efficiency, improve the exit temperature, reduce CO pollutants and emissions of UHC. Then, the compact combustion chamber TIB-3C model designed test pieces of turbine blade Jianchao, and conducted a preliminary test to verify the purpose, test results are as follows: (1) design. 45 degree angle combination jet combustion ring 55, combustion ring width 0.6, curved blade with a groove with turbine nozzle, adding pre rotation vanes of turbine blade Jianchao compact combustion chamber test (TIB-3C) model; (2) design for turbine blade Jianchao compact combustion chamber test (TIB-3C test) the system (3) to keep the total flow rate unchanged, reducing the mainstream flow, two increase in flow, will increase the total pressure loss, and the numerical simulation results, the relative error was about 10%, two are in good agreement. (4) the turbine guide vanes compared simulation test data of temperature distribution and numerical, the relative error was about 18%, and the calculation results of numerical experiments results. Finally, based on the different structure of the main gas - turbine burning between the integrated combustion chamber (MC-TIB) combustion chamber to study, the numerical study shows that: (1) MC-TIB The burning ring length width ratio directly affects the combustion space scale combustion chamber, has a direct effect on the combustion characteristics, improve combustion ring aspect ratio, is beneficial to improve the export rate, improve the exit velocity distribution, increase the outlet temperature, reduce the pressure loss; reduce the combustion ring aspect ratio, is conducive to strengthening the primary and secondary flow mixing, improve temperature distribution, reduce NOx and UHC emissions of pollutants; (2) the MC-TIB combustion chamber combustion ring jet angle directly affects the combustion flow field distribution of the fluid in the ring, the impact on the combustion performance, increase the jet angle, is beneficial to improve the export rate, improving the velocity, reduce the emission of UHC; reduce the jet angle that is conducive to the improvement of outlet temperature, improve outlet temperature distribution to reduce NOx emissions; jet angle changes had little effect on the pressure loss.

【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V231.2

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