旋转爆轰燃烧室与涡轮导向器集成特性数值研究

doi:10.7527/S1000-6893.2023.29223

Abstract

Abstract:

This study investigates the influence of cascade solidity on the flow field distribution and working characteristics of the rotating detonation combustor- turbine guide vane to further optimize the design of the rotating detonation combustor and turbine guide vane. Based on the SST k-ω viscous turbulence model， the two-dimensional unsteady Reynolds-averaged Navier-Stokes control equation is solved. Combined with the intermittent factor transition model， the detonation combustion mechanism adopts the n-decane-air single-step reaction. By applying the high temperature and high pressure zone to the initial flow field to induce the detonation wave， we conduct numerical calculation for the rotating detonation combustor with six different cascade solidity turbine guide vanes and without the turbine guide vane， respectively. The instantaneous flow field evolution and wave structure are discussed and analyzed， and the working characteristics of the turbine guide vane under different cascade solidity are evaluated. The results show that the dynamic rake-type shock envelope is formed in both upstream and downstream of the turbine guide vane， with its structure and strength affected by the cascade solidity. The detonation flow field characteristics ensure the self start ability of the cascade channel. The turbine guide vane suppresses the upstream pressure peak， and the peak attenuation rate is up to 60.87%. The total pressure gain of detonation combustion is improved； the maximum total pressure ratio at the outlet of the guide vane is 1.24， and the frequency of the outlet total pressure ratio is positively correlated with the cascade solidity， up to 143.33 kHz. The cascade passage has a certain ability to adjust the flow of detonation products. The minimum time-average deviation angle is 1.84°， the maximum time-average Mach number at the outlet is 1.38， and the uniformity of the outlet flow angle is significantly improved. The research results reveal the potential value of the turbine guide vane to the performance improvement of the continuous rotating detonation turbine engine， providing guidance for the design optimization and engineering application of the engine.

Key words: rotating detonation combustor, turbine guide vane, cascade solidity, flow field structure, working characteristics

CLC Number:

V231.1

Bowei MENG, Hu MA, Zhenjuan XIA, Changsheng ZHOU. Numerical study on characterization of integrated rotating detonation combustor and turbine guide vane[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(10): 129223.

Figures/Tables 22

Fig.1

Table 1

Fig.2

Table 2

Grid convergence error analysis

项目	$h m$ /mm	$ξ a v e$	$r c$	$e a$ /%	$e e x t$ /%	GCI/%
细网格	0.15	0.922 0
中网格与细网格对比			1.35	0.07	0.29	0.36
中网格	0.21	0.921 3
粗网格与中网格对比			1.34	0.06	0.23	0.29
粗网格	0.28	0.920 8

Table 2

Fig.3

Fig. 4

Fig.5

Fig.6

Table 3

Comparison of numerical results with theoretical parameters

计算方法	$p C J$ /MPa	$T C J$ /K	$U C J$ /（m·s^-1）
相对偏差/%	-1.74	+11.75	+0.80
数值计算	0.804	3 407.60	1 790.18
理论计算	0.818	3 007.17	1 775.80

Table 3

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig. 12

Fig.13

Fig.14

Fig.15

Fig.16

Fig.17

Fig.18

Fig.19

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模型编号	B_n	g/mm	μ
C-0	0
C-1	3	70.0	0.87
C-2	5	42.0	1.45
C-3	7	30.0	2.03
C-4	10	21.0	2.91
C-5	12	17.5	3.49
C-6	15	14.0	4.36

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Numerical study on characterization of integrated rotating detonation combustor and turbine guide vane

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