本文關(guān)鍵詞：渦輪葉間超緊湊燃燒室研究　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

  更多相關(guān)文章： 燃氣渦輪發(fā)動機 超緊湊燃燒 渦輪葉間燃燒 燃燒性能 長寬比 射流角度

【摘要】：渦輪葉間超緊湊燃燒室作為一種新型燃燒室,以其結(jié)構(gòu)緊湊,燃燒效率高,壓力損失小的特點應(yīng)用于燃氣渦輪發(fā)動機。本文在已有研究的基礎(chǔ)之上,設(shè)計了渦輪葉間燃燒室的試驗件模型(Turbine inter-Blade Burner with 3 Cavities,簡稱TIB-3C)以及與之配套的試驗系統(tǒng),進行了初步的驗證性試驗測量,并且利用CFD軟件FLUENT對試驗件簡化模型進行數(shù)值模擬,探究流量分配與操作壓力對燃燒室性能的影響。此外,本文針對不同結(jié)構(gòu)的主燃(Main Combustor,MC)-渦輪葉間補燃(Turbine inter-Blade Burner,TIB)一體化燃燒室(簡稱MC-TIB)進行了數(shù)值模擬分析,主要研究了燃燒環(huán)長寬比以及燃燒環(huán)射流角對主燃-渦輪葉間補燃一體化燃燒室性能的影響。本文首先研究了燃燒工況對渦輪葉間超緊湊燃燒室(TIB-3C)的影響,發(fā)現(xiàn):(1)在總流量保持不變的條件下,適當提高二次流流量,有利于提高出口速度,改善出口溫度分布,提高燃燒效率,降低出口污染物污染物NOx、CO以及UHC的排放,并且在較高二次流流量工況下,出口徑向平均溫度分布較理想,有利于燃燒室的設(shè)計;(2)適當?shù)脑黾尤紵业牟僮鲏毫τ欣诳倝簱p失的減少,提高燃燒效率,提高出口溫度,減少污染物CO以及UHC的排放。隨后,本文對渦輪葉間超緊湊燃燒室TIB-3C模型進行了試驗件的設(shè)計,并且進行了以驗證性為目的的初步試驗,試驗成果包括:(1)設(shè)計了燃燒環(huán)射流角度組合45°55、燃燒環(huán)長寬比0.6、渦輪導(dǎo)向器采用帶凹槽的彎曲葉片、加入了預(yù)旋葉片的渦輪葉間超緊湊燃燒室試驗件(TIB-3C)模型;(2)設(shè)計了針對渦輪葉間超緊湊燃燒室試驗件(TIB-3C)的試驗系統(tǒng)(3)保持總流量不變,減少主流流量,增加二次流流量,會導(dǎo)致總壓損失增大,并且與數(shù)值模擬計算的結(jié)果對比發(fā)現(xiàn),相對誤差在10%左右,二者吻合較好。(4)渦輪導(dǎo)向器葉片溫度分布的試驗數(shù)據(jù)與數(shù)值模擬相比,相對誤差在18%左右,試驗得出的結(jié)論與數(shù)值計算的結(jié)果吻合較好。最后,本文對不同結(jié)構(gòu)的主燃-渦輪葉間補燃一體化燃燒室(MC-TIB)燃燒室進行了數(shù)值模擬研究,研究表明:(1)MC-TIB的燃燒環(huán)長寬比直接影響了補燃室中燃燒反應(yīng)的空間尺度,對燃燒特性產(chǎn)生直接的影響,提高燃燒環(huán)長寬比,有利于提高出口速度,改善出口速度分布,增加出口溫度,減少壓力損失;降低燃燒環(huán)長寬比,有利于強化主次流摻混,改善溫度分布,降低污染物NOx以及UHC排放;(2)MC-TIB燃燒室的燃燒環(huán)射流角度直接影響燃燒環(huán)內(nèi)流體的流場分布,對燃燒性能造成影響,適當?shù)脑龃笊淞鹘嵌?有利于提高出口速度,改善速度分布,減少UHC排放;減小射流角度,有利于提高出口溫度,改善出口溫度分布,降低NOx污染物排放;射流角度的改變對壓力損失的影響較小。
[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.

【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】：V231.2

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