某回流燃烧室火焰筒冷却性能分析

doi:10.7527/S1000-6893.2022.27326

Abstract

Abstract:

To study the combustion and cooling performance of the combustion liner in the reverse-flow combustor， a combustor model was built， and failure reasons were analyzed through heat fluid-structure coupling simulation. By introducing film cooling holes with different hole types and dip angles， the cooling effect of the original defective component part was compared. The results show that the location of the maximum temperature and maximum temperature gradient of the original structural part is the same as the failure location of the actual fault part， so that it can be considered that the failure is caused by high temperature and high temperature gradient； compared with initial cooling structure， the maximum temperature of the inner wall of the reverse combustor all decreased after the hole structure change， 281.34 K at most and 60.15 K at least； with the same hole type， the cooling effectiveness is the best at a hole inclination angle of 30°， and the cooling effectiveness is the worst at the hole inclination angle of 60°. With the same hole inclination angle， the cooling effectiveness of the convergent hole is the best， because of a vortex pair opposite to the original structure generated on the section near the outlet end， therefore improving the cooling effect， while the cooling effectiveness of cylindrical holes is the worst.

Key words: reverse-flow combustor, failure, combustion, cooling hole, cooling performance, vortex pair

CLC Number:

V233.5⁺4

Weiping LI, Longjin YANG. Cooling performance analysis of combustion liner in reverse-flow combustor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(9): 127326.

Figures/Tables 17

Fig. 1

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Table 1

Performance parameters of GH3044

温度/ $K$	导热率 $/ (W · m - 1 · K - 1)$	比热/ $(J · k g - 1 · K - 1)$
373.15	11.7	440
573.15	14.2	482
773.15	17.2	524
1 073.15	21.8	566
1 273.15	26.1	629

Table 1

Fig. 4

Fig. 5

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Cooling performance analysis of combustion liner in reverse-flow combustor

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