高温降涡轮高位预旋供气系统设计

doi:10.7527/S1000-6893.2024.30672

Abstract

Abstract:

The performance of the pre-swirl system directly restricts the cooling air quality of the turbine blades in the transition state. In this paper， the forward design of the turbine pre-swirl system is carried out by applying the theory of power-heat conversion. The aerodynamic parameters of each characteristic cross section of the system are calculated according to known boundary conditions， and the flux area of each element and its structural parameters are determined. The three-dimensional physical model is constructed through the results of the one-dimensional calculations， and the structure of high-performance pre-swirl system is obtained through rotor-stator matching iteration. The characterization and performance evaluation of the pre-swirl system with high temperature drop are conducted. The results show that the relative deviations of the bleed air mass flow rate， system temperature drop and temperature drop efficiency of the one-dimensional design calculations and numerical simulation results are less than 1.5%， and the relative deviations of the system temperature drop from the corresponding experimental results are less than 1.5%， provided that the turbine blades supply air mass flow rate and supply air pressure requirements are met. The discharge coefficients of the pre-swirl nozzle， receiver hole and supply hole at the design point are 0.937， 0.716 and 0.744， respectively. The system temperature drop and temperature drop efficiency reach 61.53 K and 80%， respectively， and the specific power consumption of the system is -55.74 kW/（kg·s^-1）. Under the condition of ensuring the turbine blades supply air mass flow rate and the supply air pressure， the system temperature drop at the four cruise operating points reaches 39.73–62.88 K， and the specific power consumption reaches -55.74–-16.48 kW/（kg·s^-1）.

Key words: aero-engine, pre-swirl air supply system, one-dimensional design, high temperature-drop, low power consumption, performance evaluation

CLC Number:

V231

Xianzhao YANG, Gaowen LIU, Lingying GUO, Jiale MA, Aqiang LIN. Design of turbine high radius pre-swirl system with high temperature drop[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130672.

Figures/Tables 21

Fig.1

Fig.2

Table 1

Design requirement parameters of the pre-swirl system

参数类型	需求参数及符号
压力	系统进口总压p $0 *$ 、系统出口静压p₄
温度	系统进口总温T $0 *$
流量	引气流量m_in、供气流量m_out
转速	转速 $ω$
供气半径	供气半径r₃

Table 1

Table 2

Parameters to be solved of the pre-swirl system design

参数类型	需求参数及符号
压力	接受孔出口静压p₃、喷嘴出口静压p₁
相对总温	供气孔出口T $r e l, 4 $ 、接受孔出口T $r e l, 3 $ 、喷嘴出口T $r e l, 1 *$
静温	接受孔出口T₃、喷嘴出口T₁
气流速度	喷嘴出口周向速度V_φ，1、接受孔出口周向速度V_φ，3、接受孔入口周向速度V_φ，2、喷嘴出口轴向速度V_a，1

Table 2

Fig.3

Table 3

Table 4

Fig.4

Table 5

Comparison of CFD results and 1D calculation results

对比结果	引气流量/（kg·s^-1）	系统温降/K	$η t$
一维计算结果	1.353	61.53	0.790
CFD计算结果	1.351	60.86	0.781
相对偏差/%	0.15	1.09	1.10

Table 5

Fig.5

Table 6

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

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参数	工况点1（Ma=0.8）	工况点2（Ma=2.35）	工况点3（Ma=3.6）	工况点4（Ma=4.0）
供气半径/mm	110
涡轮动叶数目N	60
进口总压/kPa	807	1 383	633	527
进口总温/K	518.1	897	1 006.85	1 045.16
出口静压/kPa	560	970	452	377
转速/（r·min^-1）	19 812	25 634	25 073	22 750
旋转马赫数	0.503	0.502	0.465	0.415
供气流量/（kg·s^-1）	0.973 0	1.291 6	0.578 6	0.489 8
引气流量/（kg·s^-1）	1.018 47	1.353 30	0.603 00	0.509 30

结构	参数	数值
预旋喷嘴	喉部总面积A_N₁/mm²	829.93
	前缘半径r₁/mm	1.46
	固体域宽s₁/mm	8.42
	尾缘半径r₂/mm	0.15
	喷嘴叶高h₁/mm	7.31
	喷嘴栅距t₁/mm	14.62
	轴向弦长L₁/mm	11.11
接受孔	出口总面积A_R₁/mm²	3 192.84
	进口结构角β₁_k /（°）	50.56
	前缘半径r_A/mm	0.4
	出口结构角β₂_k /（°）	90
	轴向长度L/mm	10
	安装角β_y /（°）	48
	固体域周向长度L_φ，1/mm	4.61
供气孔	总面积A_S1/mm²	3 192.84
	周向角β₃_k /（°）	90
	叶高h₂/mm	7.70
	固体域周向长度L_φ，2/mm	4.61

文献	预旋系统	结构对比
本文		采用叶孔式喷嘴，动叶前缘式叶形接受孔，去除盖板腔
［27］		采用斜孔式喷嘴，斜孔形接受孔；喷嘴、接受孔和供气孔数目均为24个
［28］		采用斜孔式喷嘴，直孔形接受孔；喷嘴、接受孔和供气孔数目分别为23、36和36
［29］		采用斜孔式喷嘴，直孔形接受孔和环缝供气孔；喷嘴和接受孔数目均为36个
［30］		采用叶片式喷嘴和直孔形接受孔；喷嘴、接受孔和供气孔数目均为60个

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Design of turbine high radius pre-swirl system with high temperature drop

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