Design of Dome Structure for A Lean Premixed Swirled Combustor of Gas Turbine Based on the Numerical Method

doi:10.12096/j.2096-4528.pgt.21109

Abstract

Abstract:

To analyse the dome structure of the lean premixed swirled combustor, the influences of lance tip shapes, inflow air flow rates, numbers and locations of fuel nozzles and head expansion ratios on the combustion flame, flow field and flame dynamic response were investigated by computational fluid dynamics. The results show that the flame shape remains unchanged when the air velocity increases to a certain value. Increasing the number of fuel holes on the pressure surface, the high heat release rate area is concentrated in the root of the central recirculation zone. While increasing the number of fuel injectors on the pressure side and suction side makes the flame root temperature of the central recirculation zone lower, indicating a tendency to reduce the thermal NO _x . Increasing the flame tube diameter helps the central recirculation zone to expand radially, resulting in longer flame branches. The axial length of flame will be shortened by changing the centre-lance tip from flat to ellipse. The amplitude and phase of flame transfer function are not affected by changing the centre-lance tip face shape, but the phase of flame transfer function is obviously changed by increasing the number of fuel holes.

Key words: gas turbine, swirled premixed combustor, dome structure, fuel nozzle configuration, combustion characteristic, numerical simulation

CLC Number:

TK 47

Yang YANG, Yaoqiang LI, Jinqi ZHANG. Design of Dome Structure for A Lean Premixed Swirled Combustor of Gas Turbine Based on the Numerical Method[J]. Power Generation Technology, 2023, 44(5): 712-721.

Figures/Tables 19

Fig. 1 Axial swirler and geometric model for numerical calculation

Fig. 2 Geometric structure and corresponding parameters of calculation domain of single-head combustor

Tab. 1 Boundary conditions of cases with different velocities and mass flow rates

边界	参数	空气进口	燃料吸力面	燃料压力面	燃烧器出口	燃料质量分数/%
1	速度/(m/s)	18.00	25.64	26.30	11.98	2.9
1	流量/(g/s)	19.87	0.30	0.30	20.47	2.9
2	速度/(m/s)	35.00	49.90	51.18	22.54	2.9
2	流量/(g/s)	38.63	0.58	0.58	39.80	2.9
3	速度/(m/s)	50.00	60.22	61.77	29.93	2.5
3	流量/(g/s)	55.19	0.70	0.70	56.59	2.5
4	速度/(m/s)	50.00	71.23	73.07	32.20	2.9
4	流量/(g/s)	55.19	0.83	0.83	56.85	2.9
5	速度/(m/s)	75.00	106.85	109.60	48.25	2.9
5	流量/(g/s)	82.79	1.24	1.24	85.28	2.9

Tab. 2 Parameters and boundary conditions of different fuel nozzles

工况	孔数	压力面喷孔			吸力面喷孔
工况	孔数	面积/mm²	速度/(m/s)	流量/(g/s)	面积/mm²	速度/(m/s)	流量/(g/s)
基准型	压力面、吸力面各2孔	17.9	71.23	0.83	17.4	73.07	0.83
改型1	压力面、吸力面各4孔	34.9	36.57	0.83	34.4	37.05	0.83
改型2	压力面4孔	34.9	73.13	1.66	0	0	0
改型3	吸力面4孔	0	0	0	34.4	74.09	1.66

Fig. 3 Comparison of swirl numbers of velocity base and momentum base at each axial position sections

Fig. 4 Radial distribution of three velocity components at three different axial positions

Tab. 3 Different air flow rates and corresponding thermal power conditions

参数	工况
参数	1	2	3	4
空气流速/(m/s)	18	35	50	75
折算热功率/(MW/MPa)	0.332	0.645	0.921	1.383

Fig. 5 Heat release rate at different air flow rates

Fig. 6 Integral distribution of heat release rate of cross sections at different axial positions

Fig. 7 Cloud pictures of mass fraction of OH groups in combustion intermediates at different air flow rates

Tab. 4 Different fuel hole structures

结构	压力面燃料孔个数	吸力面燃料孔个数
基准型	2	2
改型1	4	4
改型2	4	0
改型3	0	4

Fig. 8 Distribution of heat release rate under different fuel nozzles

Fig. 9 Mass fraction distribution of OH at different fuel nozzles

Fig. 10 Heat release rate of four different head structures

Fig. 11 Cloud diagrams of mass fraction distribution of OH groups in combustion intermediates with four different head structures

Fig. 12 Cloud diagram of mass fraction distribution of H2O, the final combustion product with four different head structures

Fig. 13 Axial velocity cloud images of four different head structures

Fig. 14 Streamlines of axial velocity components of four different head structures

Fig. 15 Amplitude and phase of flame transfer function for three different head structures

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