对转桨扇起飞工况气动及离散噪声特性研究

王汉义; 单鹏; 周亦成

doi:10.13224/j.cnki.jasp.20230672

对转桨扇起飞工况气动及离散噪声特性研究

doi: 10.13224/j.cnki.jasp.20230672

1.
北京航空航天大学能源与动力工程学院，北京 100191
2.
中国航空发动机集团有限公司中国航空发动机研究院，北京 101304

详细信息

作者简介:
王汉义（1987-），男，博士生，主要从事发动机气体动力学与气动声学研究。E-mail：wanghanyi@buaa.edu.cn

中图分类号: V231
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出版历程
- 收稿日期: 2023-10-23
- 网络出版日期: 2025-07-13

Aerodynamic and discrete frequency noise characteristics of contra-rotating propfans under take-off conditions

1.
School of Energy and Power Engineering，Beihang University，Beijing 100191，China
2.
Aero Engine Academy of China，Aero Engine Corporation of China，Beijing 101304，China

摘要

摘要:
为在对转桨扇的气动设计反问题阶段进行气动优化设计与低噪声特性设计，基于Farassat推导的Ffowcs Williams-Hawkings方程时域解公式Formu 1A，全新编写了对转桨扇离散噪声计算程序FODNOPPa2。对一台用可压升力面理论设计的对转桨扇模型CRPFt，在飞行高度为300 m，飞行马赫数为0.24的起飞工况下，得到了分布在5条典型型线上与机身同步运动观测点处的对转桨扇气动离散噪声。其中用计算流体力学软件NUMECA FINE™/Turbo的非线性谐波求解器获得三维黏性准非定常流场，提取噪声计算的输入气动载荷。结果表明：非线性谐波法可准确地计算出CRPFt在起飞工况下的三维黏性准非定常流场。在两桨中间平面附近的观测点处转子谐波的声压级（SPL）较大，在距离中间平面较远的观测点处干涉谐波的声压级较大。
- 对转桨扇 /
- 离散噪声 /
- 时域方法 /
- 延迟时间方程 /
- 非线性谐波法
Abstract:
To carry out the aerodynamic optimization design and the low-noise-characteristic design of the contra-rotating propfans in the aerodynamic design inverse problem phase, a program FODNOPPa2, specifically for predicting the discrete frequency noise, was recently developed. Based on the formulation Formu 1A derived by Farassat, this program offered the time-domain solutions of the Ffowcs Williams-Hawkings equation. By utilizing this program, the discrete frequency noise of a model contra-rotating propfans called CRPFt, which was designed using compressible lifting surface theory, was acquired under the take-off condition with a flying altitude 300 m and a Mach number 0.24. Observation points were synchronized with the movement of the fuselage and distributed across five representative lines or curves. Utilizing the nonlinear harmonic solver available in the computational fluid dynamics software NUMECA FINE™/Turbo, it tried to acquire a three-dimensional viscous quasi-unsteady flow field and to extract the aerodynamic loads as the input of the noise calculation. This study demonstrated that the nonlinear harmonic approach was capable of effectively simulating the three-dimensional viscous quasi-unsteady flow field of CRPFt under the take-off condition. Typically, the sound pressure level (SPL) of the rotor harmonics held a greater significance than the SPL of the interference harmonics at the observation points situated in close proximity to the middle plane between the two propfans. Nevertheless, the SPL of the interference harmonics had more significance when measured at the observation points located further away from the middle plane.
- contra-rotating propfans /
- discrete frequency noise /
- time-domain method /
- retarded time equation /
- nonlinear harmonic method

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图 1 CRPFt的几何和流场计算域

Figure 1. Geometry and flow-field calculation domains for CRPFt

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图 2 两种程序计算的CRPFt起飞工况下的总噪声

Figure 2. Overall noise of CRPFt under take-off condition calculated separately by two codes

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图 3 t = 0时刻CRPFt流场r/R = 0.8圆柱截面的静压、相对马赫数、熵的分布

Figure 3. Distribution of static pressure, relative Mach number and entropy of CRPFt at r/R = 0.8 cylindrical section at time t = 0

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图 4 NUMECA NLH计算的CRPFt的性能变化曲线

Figure 4. Performance variation curves calculated with NUMECA NLH for CRPFt

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图 5 CRPFt噪声观测点的分布

Figure 5. Distribution of noise observation points for CRPFt

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图 6 水平直线段LinH中间观测点处单个、两个转子产生离散噪声的时序声压变化曲线

Figure 6. Time series acoustics pressure variation curves of discrete noise generated by single and two rotors at middle observation point of horizontal line segment LinH

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图 7 沿水平直线段LinH两个转子离散总噪声主要谐波声压级的变化

Figure 7. Sound pressure level variations of dominant harmonics of overall discrete noise of two rotors along horizontal line segment LinH

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图 8 沿水平直线段LinH两个转子离散噪声的分组谐波总声压级的变化

Figure 8. Overall sound pressure level variations of grouped harmonics of discrete noise of two rotors along horizontal line segment LinH

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图 9 沿水平直线段LinH单个、两个转子离散噪声总声压级的变化

Figure 9. Overall sound pressure level variations of discrete noise of single and two rotors along horizontal line segment LinH

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图 10 沿竖向直线段LinVU单个、两个转子离散噪声总声压级的变化

Figure 10. Overall sound pressure level variations of discrete noise of single and two rotors along vertical line segment LinVU

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图 11 沿竖向直线段LinVD单个、两个转子离散噪声总声压级的变化

Figure 11. Overall sound pressure level variations of discrete noise of single and two rotors along vertical line segment LinVD

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图 12 沿半径为1.5R的子午面内圆周CirC单个、两个转子离散噪声总声压级的指向性

Figure 12. Directivity of overall sound pressure level of discrete noise of single and two rotors along circle CirC of radius 1.5R in meridional plane

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图 13 沿半径为1.5R的轴向横截面圆周CirA单个、两个转子离散噪声总声压级的指向性

Figure 13. Directivity of overall sound pressure level of discrete noise of single and two rotors along axial cross-sectional circle CirA of radius 1.5R

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表 1 CRPFt的来流流场、几何和运动主要参数

Table 1. Key incoming flow field, geometry and kinematic parameters of CRPFt

参数	前桨	后桨
飞行高度H/m	300
飞行速度υ_x, υ_y, υ_z/（m/s）	0, 0, −81.39
未扰动空气密度ρ₀/（kg/m³）	1.19
声速c₀/（m/s）	339.141
叶片数N_F、N_R	8	6
叶尖直径D =2R/m	0.622	0.622
轮毂半径r_h/m	0.072	0.072
相对半径$ \bar r $=r/R=0.75处基元叶型桨距角ϕ_0.75/（°）	37.9	37.4
额线相对气流角β_0.75/（°）	14.3	14.3
攻角α_0.75/（°）	23.6	23.1
转速n_F、n_R/（r/min）	−9814.37	+9814.37
角速度ω_F、ω_R/（rad/s）	−1027.76	+1027.76
叶尖相对马赫数Ma_hel	0.97	0.97

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表 2 流场边界条件

Table 2. Flow-field boundary conditions

边界	条件
进口 Inlet	总压p_t = 101772.35 Pa；总温T_t = 289.5 K；来流速度方向沿+z，与转轴平行
出口Outlet	径向平衡；径向位置r =1.9 m处静压p = 97772.7 Pa
远场External	静压p = 97772.7 Pa；静温T = 286.2 K；气流速度（υ_x, υ_y, υ_z） = （0, 0, 81.394） m/s
叶片表面y⁺	最大值<9；除前缘附近，叶片表面绝大部分区域< 3

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表 3 流场准非定常参数

Table 3. Flow-field quasi-unsteady parameters

参数	前桨	后桨
每个转子所受扰动个数N_pertb	1
每个扰动的频率个数N_freq	3
当前转子的叶片数N_cur	8	6
相邻转子的叶片数N_adj	6	8
当前转子的转速n_cur/（r/min）	−9814.37	+9814.37
相邻转子的转速n_adj/（r/min）	+9814.37	−9814.37
当前转子相对相邻转子的转速\|n_cur−n_adj\|/（r/min）	19628.74	19628.74
扰动基础谐波的角频率（2π×\|n_cur−n_adj\|/60×N_adj）/ （rad/s）	12333.10	16444.14

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表 4 桨扇CRPFt模拟与桨扇F7A7t试验性能参数对比

Table 4. Comparison of performance parameters between simulation of CRPFt and test of F7A7t

参数	CRPFt	F7A7t
飞行高度H/m	300	0
飞行马赫数Ma	0.24	0.24
前后桨直径D/m	0.622	0.622
进距比J=υ/（Dn_s）	0.8	0.8
桨距角（ϕ_0.75F/ϕ_0.75R）/（°）	37.9/37.4	37.9/37.4
扭矩比Q_R/Q_F	1.22	1
功率系数C_P	1.93	1.63
推进效率η	0.487	0.51

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表 5 桨扇CRPFt与桨扇F7A7t的巡航设计点气动参数

Table 5. Aerodynamic parameters of CRPFc and F7A7c at cruise design point

参数	CRPFc	F7A7c
设计方法	可压缩升力面法	与涵道风扇设计相仿的准三维方法
飞行高度H/km	11	10.668
飞行马赫数Ma	0.8	0.72
前后桨直径D/m	0.622	0.622
进距比J=υ/（Dn_s）	3.14	2.8
叶尖切向速度u/（m/s）	236	239.62
叶片数N_F/N_R	8/6	8/8
叶尖后掠角（ϕ_F/ϕ_R）/（°）	41.4/41.4	33/29
单位面积桨盘载荷（P/D²）/ （kW/m²）	413.6	455.3
功率系数C_P	2.67	2.70
轮毂比$ {\bar r_{\text{h}}} $= r_h/R	0.23	0.42
总效用因子T_af	3010	2400

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表 6 准非定常模拟的CRPFt在t = 0时刻的性能

Table 6. Performance of CRPFt at time t = 0 in quasi-unsteady simulation

参数	前桨	后桨	两桨
单位面积桨盘载荷（P/D²）/（kW/m²）	1090.1	1328.6	2418.7
功率P/kW	421.74	514.03	935.77
拉力F/N	2516.5	3085.9	5602.4
秒转速n_s/（r/s）	163.57	163.57
功率系数C_P=P/（ρ₀$ n_{\text{s}}^3 $D⁵）	0.87	1.06	1.93
拉力系数C_F=F/（ρ₀$ n_{\text{s}}^2 $D⁴）	0.528	0.648	1.176
推进效率η	0.4857	0.4886	0.4873

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表 7 CRPFt准非定常模拟的总体参数C_F、C_P、η 随时间变化曲线的周期

Table 7. Period of time-dependent curves of overall parameters C_P, C_F and η in quasi-unsteady simulation for CRPFt

类别	j阶谐波参数（j=1, 2, 3）		瞬时参数（平均参数与1阶、2阶、3阶各谐波参数的和）
类别	以时间表示的周期 T_j/s	以角度表示的周期 Θ_j/（°）	以时间表示的周期T/s	以角度表示的周期Θ/（°）
前桨叶片F1～F8	T_Fj=60/（\|n_F-n_R\|/N_R）/j=T/（12j）	Θ_Fj=（360/12）/j=30/j	T_F=T/12	Θ_F=30
后桨叶片R1～R6	T_Rj=60/（\|n_R-n_F\|/N_F）/j=T/（16j）	Θ_Rj=（360/16）/j=22.5/j	T_R=T/16	Θ_R=22.5
F1～F8与 R1～R6的和	T_FRj=3T_Fj=4T_Rj=T/[（12,16 最大公约数）×j]=T/（4j）	Θ_FRj=3Θ_Fj=4Θ_Rj=（30,22.5 最小公倍数）/j=90/j	T_FR=3T_F=4T_R=T/4	Θ_FR=3Θ_F=4Θ_R=90
前桨	T/（12×4j）=T/（48j）	30/（4j）	T/48	7.5
后桨	T/（16×3j）=T/（48j）	22.5/（3j）	T/48	7.5
两桨	T/（48j）	90/（12j）	T/48	7.5

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表 8 CRPFt准非定常模拟的叶片总体参数C_F、C_P、η随时间变化曲线的相位、波形

Table 8. Phase and waveform of time-dependent curves of blade overall parameters C_P, C_F and η in quasi-unsteady simulation for CRPFt

叶片	相位	波形
前桨	F2～F8比F1～F7对应滞后7.5°	F5～F8与F1～F4对应相同
后桨	R2～R6比R1～R5对应超前7.5°	R4～R6与R1～R3对应相同

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表 9 CRPFt噪声观测点的坐标

Table 9. Coordinates of noise observation points for CRPFt

观测点分布型线	x/m	y/m	z/m	θ/（°）, i
轴平行线段（LinH）	0	1.5R	1.5Rcot θ_H−0.1	θ_H =10i+20, i=1～13
上部直线段（LinVU）	0	（1+0.1i）R	−0.1	i=1, 2, ···, 30
下部直线段（LinVD）	0	−350+50i	−0.1	i=1, 2, ···, 6
子午截面圆（CirC）	0	1.5Rsin θ_C	1.5Rcos θ_C−0.1	θ_C=10i−10, i=1～37
轴向截面圆（CirA）	−1.5Rcos θ_A	1.5Rsin θ_A	−0.1	θ_A=10i−10, i=1～37

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