端区边界层扭曲对高负荷涡轮二次流的影响

doi:10.7527/S1000-6893.2025.32394

Abstract

Abstract:

The inlet boundary layer skew caused by rotor-stator interaction significantly influences the development of the secondary flow in high-lift low-pressure turbine. For high-lift low-pressure turbines used in civil turbofan engines， the method of combining experiment and numerical simulation was employed to investigate the influence mechanisms of inlet boundary layer skew on the development and evolution of secondary flows under wake sweep. Furthermore， the relative contributions of incoming wakes and boundary layer skew to secondary flow development were systematically quantified. The results indicate that， at an inlet Reynolds number of 1×10⁵ and turbulence intensity of 2.5%， endwall boundary layer skew reduces secondary flow and flow loss. This occurs by enhancing shear layer instability between the endwall-region fluid and the mainstream， while simultaneously weakening the transverse pressure gradient across the cascade channel. Increasing the rotational speed of the rotating endwall intensifies boundary layer skew， leading to thickening of the leading-edge boundary layer. This promotes secondary flow development and increases flow loss. Upstream wake further promotes shear layer instability， thereby weakening the secondary flow. However， the mixing dissipation associated with the wake adversely impacts the overall aerodynamic performance of the low-pressure turbine. At the position of 40% axial chord length downstream of the cascade， boundary layer skew reduces flow loss by approximately 3.45% compared to the baseline. Conversely， intensification of boundary layer skew increases flow loss by nearly 6.25%. The mixing dissipation from the upstream wake contributes a further flow loss increase of about 10.08% relative to the case with intensified skew.

Key words: high-lift low-pressure turbine, end zone secondary flow, end zone boundary layer skew, incoming wakes, unsteady flow

CLC Number:

V231.3

Liunan LI, Xiao QU, Yanfeng ZHANG, Xingen LU, Junqiang ZHU. Effect of end zone boundary layer skew on secondary flow in high-lift turbine[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(5): 132394.

Figures/Tables 31

Fig.1

Fig.2

Fig.3

Table 1

Fig.4

Fig.5

Table 2

Grid node parameters of computational domain

块	网格节点数
块	定常计算域	非定常计算域
1	97×77	49×13
2	17×17	17×29
3	49×37	17×13
4	17×17	49×97
5	17×289	17×73
6	17×121	17×73
7	17×185	93×85
8		17×17
9		17×17
10		17×261
11		17×109
12		17×169
Total	19 975	26 232
Y $m a x +$	0. 502	0.456

Table 2

Fig.6

Fig.7

Table 3

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

Fig.17

Table 4

Table 5

Fig.18

Fig.19

Fig.20

Fig.21

Fig.22

Fig.23

Table 6

Fig.24

Fig.25

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叶型参数	数值
弦长/mm	86.2
轴向弦长/mm	75.4
栅距/mm	66.8
叶高/mm	200
几何进气角/（°）	40.5
几何出气角/（°）	61.3
载荷系数（Z_w）	1.1

物理时间步	时间步长/（10^-5 s）	叶型损失Y_p	绝对误差ΔY_p
30	9.08	0.041 160
50	5.45	0.044 318	3.16×10^-3
60	4.54	0.045 116	7.98×10^-4
80	3.41	0.045 244	1.28×10^-4
100	2.73	0.044 798	-4.46×10^-4

工况	Y	ΔY/%
基准工况	0.116
ϕ=1.07	0.112	-3.45
ϕ=1.34	0.114	1.78
ϕ=1.60	0.117	2.63
ϕ=2.14	0.119	1.71
ϕ=2.14+尾迹	0.131	10.08

参数	基准工况	ϕ=1.07	ϕ=2.14	ϕ=2.14+尾迹
边界层厚度/mm	20.6	23.7	24.9	21.3
位移厚度/mm	2.27	2.31	2.44	2.07
动量厚度/mm	1.49	1.71	1.78	1.49
形状因子	1.52	1.35	1.37	1.39

监测点	h/B_x	y/B_x	z/B_x
1	0.021	0.239	-0.199
2	0.021	0.060	-0.040
3	0.050	-0.225	0.531
4	0.289	0.332	0.968

Effect of end zone boundary layer skew on secondary flow in high-lift turbine

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