高性能涡轮低位预旋供气系统正向设计

doi:10.7527/S1000-6893.2024.30832

Abstract

Abstract:

Given that it is difficult for reverse design of imitation reconstruction method to meet the performance requirements of the advanced aero-engine pre-swirl system， this paper proposes an original forward design framework. Starting from design point parameters， the framework establishes a forward design process for the pre-swirl system， adopting the vane shaped hole nozzle and oblique receiver hole. Through one-dimensional design calculation， the aerodynamic parameters along the characteristic cross-section at the design point of the pre-swirl system， the specific geometrical structural parameters of the characteristic components， are obtained， along with a preliminary prediction of the system temperature drop performance. The results of one-dimensional design are then calibrated through three-dimensional calculation. The performance improvement evaluation of the flow and temperature drop characteristic of the pre-swirl system based on forward design is carried out， with emphasis on revealing the influence of the angle of attack of the airflow at the inlet of the receiver hole on the performance of the system. The study shows that the average deviation of the flow rate between the one-dimensional design and the three-dimensional calculation of the pre-swirl system is only 0.8%， and the average deviation of the system temperature drop efficiency is only 5.12%. Combining the entropy increase， temperature drop， power consumption， and other performance parameters of the system， the range of angle of attack at the inlet of the receiver hole when the system performance parameters are stable is-7° to 3°， indicating that it is feasible to improve the performance of the system based on the forward design method. The discharge coefficient of the vane shaped hole pre-swirl nozzle is 10.63% higher than that of the hole-type nozzle， and 4.58% higher than that of the cascade vane nozzle. The results also show that flow loss in the rotating zone is reduced by using oblique receiver holes， and the area resistance is lowered. The temperature drop efficiency of the low-radius pre-swirl system designed by the forward design method is 66%， which is more than 45.2% higher compared to the overall level of the low-radius pre-swirl system.

Key words: aero-engine, pre-swirl system, forward design, performance improvement, power consumption, temperature drop

CLC Number:

V231

Guanwei YAO, Gaowen LIU, Yan CHEN, Xiaozhi KONG, Aqiang LIN. Forward design of high-performance turbine low-radius pre-swirl system[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(7): 130832.

Figures/Tables 21

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预旋喷嘴型式	偏转角/（°）	流量系数范围	落后角范围/（°）
直孔型	15~30	0.7~0.8	<0.5
气动孔型	15~30	0.8~0.9	<0.5
弯片式	10~20	0.8~0.9	1.0~3.0
叶片型	10~20	0.85~0.95	0.5~2.0
叶孔型	10~20	0.85~0.95	<0.5

参数	设计点1	设计点2	设计点3	设计点4
供气半径/mm	110	110	110	110
涡轮动叶数目N	60	60	60	60
进口总压/kPa	1 383	807	633	527
进口总温/K	897	518.1	1 006.85	1 045.16
出口静压/kPa	970	560	452	377
转速/（r∙min^-1）	25 634	19 812	25 073	22 750
供气流量/（kg∙s^-1）	1.353 3	0.973 0	0.578 6	0.489 8
引气流量/（kg∙s^-1）	1.291 63	1.018 47	0.603	0.509 3
旋转雷诺数Re_ϕ /10⁶	3.145	3.456	1.192	1.184
旋转马赫数Ma_ϕ	0.502 0	0.502 9	0.465 0	0.414 5

特征元件	参数	数值
预旋喷嘴	喉部总面积A_N/mm²	786.37
	前缘半径r₁/mm	1.59
	尾缘半径r₂/mm	0.16
	栅距t₁/mm	15.88
	固体域宽s₁/mm	1.40
	叶高h₁/mm	7.94
	轴向弦长L₁/mm	12.07
接受孔	出口总面积A_R/mm²	3 451.76
	进口结构角β_1k/（°）	23.13
	轴向长度L/mm	6
	固体域周向长度L_ϕ_，1/mm	6.91
供气孔	总面积A_S/mm²	3 217.43
	与周向的夹角β_3k/（°）	90
	叶高h₁/mm	7.31
	固体域周向长度L_ϕ_，2/mm	4.61

设计点	理想温降/K	预旋喷嘴温降/K	系统温降/K	系统温降效率/%
1	77.90	67.66	50.64	65
2	50.00	42.94	31.91	64
3	81.65	66.79	50.82	62
4	83.81	61.11	48.04	57

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Forward design of high-performance turbine low-radius pre-swirl system

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