基于URANS/TPP模型的风扇转静干涉单音噪声预测

doi:10.7527/S1000-6893.2023.28543

Abstract

Abstract:

In order to solve the problem of three-dimensional high-precision evaluation of fan noise， a numerical prediction method for the fan rotor-stator interaction noise is successfully proposed based on the Unsteady Reynolds Average Numerical Simulation （URANS） model and the Triple Plane Pressure （TPP） mode matching model. The feasibility of the URANS model for tone noise calculation in the duct is analyzed， and an error control criterion is established. On this basis， the URANS model is used to obtain the unsteady flow field of the fan， and the noise source is extracted using the TPP mode matching method to obtain the modal characteristics of the noise in the duct. Based on the experimental data of a large bypass ratio scaled fan， the accuracy of the model is compared and verified. The results show that the model is able to reliably predict the rotor-stator interaction noise. In addition， the design of low-noise blades based on the leaned and swept stator is carried out. The three-dimensional flow and acoustic fields are analyzed based on the proposed numerical model. The suppression mechanism of rotor-stator interaction noise sources is explored to support the design of low-noise fans.

Key words: fan tone noise, rotor-stator interaction, unsteady Reynolds average, Triple Plane Pressure, leaned and swept stator

CLC Number:

V231.3

Yunan CAI, Liang JI, Danwang LI, Ye XIA, Zhen NI. Fan rotor-stator interaction noise prediction based on URANS/TPP model[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(22): 128543-128543.

Figures/Tables 19

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Table 1

Order and prediction error of dominant acoustic modal under different operation conditions

工况	BPF阶数	周向模态阶数	误差/dB
OP1，后传	1	$1 × F = 18$	4.4
	2	$2 × F - 1 × S O G V = - 19$	1.9
	2	$2 × F = 36$	-5.3
OP2，后传	1	$1 × F = 18$	11.5
	2	$2 × F - 1 × S O G V = - 19$	2.7
	2	$2 × F = 36$	2.9
OP3，后传	2	$2 × F - 1 × S O G V = - 19$	11.7
OP3，后传	3	$3 × F - 1 × S O G V = - 1$	-1.1
OP3，前传	2	$2 × F - 1 × S O G V = - 19$	-4.2
	3	$3 × F - 1 × S O G V = - 1$	1.4
	3	$3 × F - 1 × S S 0 = - 13$	4.8

Table 1

Fig.12

Fig.13

Table 2

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Table 3

References 33

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气动性能	弯掠静子	基准构型	变化量/%
外涵流量/（kg·s^-1）	99.17	99.08	0.09
外涵压比	1.559	1.563	-0.26

方法	1BPF/dB	2BPF/dB
三维升力面方法	2.32	3.91
URANS/TPP方法	4.04	1.74

[1]	MA Yiyang, ZHAO Qijun, ZHAO Guoqing. Dynamic stall control of rotor airfoil via trailing-edge flap [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(3): 120312-120312.
[2]	ZHANG Weiguang, WANG Xiaoyu, SUN Xiaofeng. Passive control of fan noise by vane sweep and lean [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(2): 120265-120273.
[3]	DENG Xiang-yang;ZHANG Hong-wu;HUANG Wei-guang. Effects of Upstream and Downstream Stators on Rotor Tip Flow in a Low-speed Axial Compressor [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2005, 26(5): 535-539.

Fan rotor-stator interaction noise prediction based on URANS/TPP model

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