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浙江大学学报(工学版)
浙江大学学报(工学版)  2021, Vol. 55 Issue (10): 2002-2012    DOI: 10.3785/j.issn.1008-973X.2021.10.023
航空航天技术     
微型涡喷发动机燃烧室全覆盖气膜冷却
王子硕(),唐豪*(),刘禹
南京航空航天大学 江苏省航空动力系统重点实验室，江苏 南京 210016
Full-coverage film cooling in combustor of micro gas turbine
Zi-shuo WANG(),Hao TANG*(),Yu LIU
Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
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摘要：

为了延长微型涡喷发动机燃烧室的使用寿命，针对燃烧室壁面高温区进行全覆盖气膜冷却研究. 在KJ-66微型涡喷发动机试车实验的基础上，比较实际燃烧工况下，排布方式和燃烧室外环的扩张孔对气膜冷却效果及燃烧室整体性能的影响. 结果表明，在实际微型涡喷发动机模型中，顺排的平均综合冷却效率低于叉排，但对壁面的综合降温效果优于叉排. 随着扩张孔出口直径的增大，气膜冷却效果逐渐改善，但会影响燃烧室出口温度分布的均匀性. 由于燃烧室后排冷却孔的影响，二次流射入主流会发生偏转，提升了气膜的冷却效果. 整体而言，全覆盖气膜冷却在实际燃烧工况下对燃烧室壁面有着很好的冷却作用，扩张型气膜孔能够有效改善燃烧室外环的气膜冷却效果.
关键词： 微型涡喷发动机燃烧室;  全覆盖气膜冷却;  扩张型气膜孔;  冷却效率;  燃烧室性能    
Abstract:

The full-coverage film cooling was analyzed for the high temperature area on combustor in order to prolong the service life of the micro gas turbine combustor. The effects of arrangements and outer ring expansion film holes on the film cooling and the overall performance of combustor were compared under the actual conditions based on the test of KJ-66 micro gas turbine. Results showed that the average overall cooling efficiency of the order arrangement was lower than that of the cross arrangement in the actual micro gas turbine model, but the comprehensive cooling effect was higher. The film cooling effect was gradually improved as the outlet diameter of expansion holes increased, but the uniformity of temperature distribution at the combustor outlet was decreased. The secondary flow into the mainstream was deflected due to the influence of the cooling holes at the back of the combustor, which can improve the effects of film cooling. The full-coverage film cooling has a good cooling effect on the combustor wall under actual combustion conditions. Expansion film holes can effectively improve the film cooling effects of the combustor outer ring.
Key words: micro gas turbine combustor    full-coverage film cooling    expansion film hole    cooling efficiency    combustor performance
收稿日期: 2020-12-15 出版日期: 2021-10-27
CLC:  V 231  
基金资助: 国家自然科学基金资助项目（91641131，51076064）
通讯作者: 唐豪     E-mail: zishuo96@163.com;hao.tang@nuaa.edu.cn
作者简介: 王子硕（1996—），男，硕士生，从事热能工程的研究. orcid.org/0000-0002-7364-4144. E-mail： zishuo96@163.com
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王子硕
唐豪
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引用本文:

王子硕,唐豪,刘禹. 微型涡喷发动机燃烧室全覆盖气膜冷却[J]. 浙江大学学报(工学版), 2021, 55(10): 2002-2012.

Zi-shuo WANG,Hao TANG,Yu LIU. Full-coverage film cooling in combustor of micro gas turbine. Journal of ZheJiang University (Engineering Science), 2021, 55(10): 2002-2012.

链接本文:

https://www.zjujournals.com/eng/CN/10.3785/j.issn.1008-973X.2021.10.023    或    https://www.zjujournals.com/eng/CN/Y2021/V55/I10/2002

图 1  KJ-66微型涡喷发动机实物与三维模型的对比图
图 2  微型涡喷发动机的试车台
图 3  微型涡喷发动机的局部测量示意图
图 4  原模型（上）和布置气膜冷却孔模型（下）的计算域
图 5  顺排与叉排气膜冷却孔示意图
图 6  不同扩张结构气膜孔的示意图
模型 排布方式 D1/mm D2/mm
So 顺排 0.3 0.3
Sc 叉排 0.3 0.3
S1 顺排 0.3 0.5
S2 顺排 0.3 0.65
S3 顺排 0.3 0.8
表 1  不同结构气膜孔的设计方案
边界 qm /(kg·s?1) pt /Pa T /K
空气进口 0.0267 3000 385
燃料进口 0.000567 N/A 300
出口 N/A 0 875
表 2  1/6周期性计算域的进出口边界条件
网格编号 N h/mm ξ
1 29 855 981 0.17 0.053 2
2 16 609 928 0.21 0.053 3
3 7 212 916 0.27 0.054 1
4 5 671 429 0.30 0.055 3
表 3  网格收敛性验证的相关计算参数
图 7  离散化计算的相对误差
图 8  局部加密的计算域网格
图 9  KJ-66微型涡喷发动机试车实验与模拟结果对比图
图 10  100 000 r/min工况下燃烧室中心截面的温度云图
图 11  100 000 r/min工况下燃烧室壁面温度云图
图 12  燃烧室内、外环上的平均综合气膜冷却效率
图 13  不同排布方式的气膜孔中心截面温度云图
图 14  外环上不同排布气膜孔的壁面温度云图
图 15  内环上不同排布气膜孔的壁面温度云图
图 16  外环上不同排布气膜孔的流线图
图 17  内环上不同排布气膜孔的流线图
模型 η ξ OTDF T1 /K T2 /K
S 0.952 0.0533 0.423 1075 1021
So 0.951 0.0533 0.440 958 823
Sc 0.952 0.0536 0.466 1004 849
表 4  不同排布气膜孔模型的燃烧室整体评价参数
图 18  外环不同扩张孔模型的平均综合气膜冷却效率
图 19  外环不同扩张孔模型的中心截面温度云图
图 20  外环不同扩张孔模型的壁面温度云图
模型 η ξ OTDF T3/K
S1 0.951 0.0536 0.470 906
S2 0.953 0.0520 0.487 823
S3 0.949 0.0526 0.500 776
表 5  不同扩张孔模型的燃烧室整体评价参数
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