新型可逆式弯掠组合叶片的研究
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摘要
正反向可逆式通风对于矿井、隧道等场合的安全生产具有极其重要的意义,具有直接反转特点的可逆式风机由于结构简单、反风响应快等特点,已成为正反向可逆式通风领域的主要研究方向。此外,在轴流风扇／压气机领域,弯掠叶片技术的应用可大幅提高气动效率、降低气动噪声、提高稳定工作范围,亦逐渐成为叶轮机械研究领域的主要研究方向之一。
本文以直接反转可逆式通风和弯掠叶片技术为研究对象,采用实验、理论和数值模拟等研究手段,首先研究了一种具有直接反转特点完全可逆式组合叶片的轴流风机。其次,在国内首次对具有相同几何参数和弯角大小的周向前弯和周向后弯动叶轮进行了对比研究,探讨了弯掠叶片的气动-声学特性及其内部流动机理,并进一步完善了适用于弯掠叶片气动计算的“双激盘”理论模型。最后,通过将弯掠叶片技术与组合叶片相结合,首次提出并研究了一种新型弯掠组合叶片。本文的主要研究工作包括：
1.叶轮设计
本文以目前工业通风领域广泛采用的T35型轴流风机作为设计原型,分别设计制造了周向前弯叶轮、周向后弯叶轮、可逆式组合叶轮和可逆式弯掠组合叶轮等四个叶轮。由于目前弯掠叶片领域尚未建立一套成熟的设计体系,本文首次尝试将逆向工程设计方法应用于弯掠叶片设计领域,建立了一套弯掠叶片逆向工程设计流程；此外,考虑到叶栅稠度沿叶高的变化,引入相对栅距系数T'作为叶片周向最佳组合参数的衡量指标,通过多方案分析成功将平面叶栅实验优化结果应用于可逆式组合叶片和弯掠组合叶片的设计。
2.实验装置及测试方法
本文建立了一套风机气动-声学实验装置。采用五孔探针和热线风速仪(CTA)对实验风机出口流场进行了详细测量,探讨了旋转单斜丝热线测量叶轮机械出口三维平均流场的方法,通过采用反射式红外跟踪触发系统,实现了同步触发多点采样平均技术在本文热线测试工作中的应用,通过分析热线单丝斜探头旋转次数和测量时测量数据总体平均次数对测试结果的影响,为热线的准确测量提供了依据。实验结果表明,本文所采用的实验装置和测试方法满足风机总体气动-声学性能及风机出口详细流场测量的要求。
3.弯掠叶片的理论与实验研究
弯掠动叶的径向力分量可有效控制通道内部径向压力梯度和叶片表面附面层中低能流体的流动,应用前弯技术有助于减小叶顶处通道二次流损失、减薄叶片表面附面层厚度、减少附面层内低能流体向叶顶处的堆积,极大改善了叶顶流动状况,有助于提高风机总体气动-声学性能；动叶后弯引起叶片下半叶高附面层内低能流体向叶片顶部迁移,增加了叶顶部分通道二次流和端壁损失,而下半叶高通道二次流损失和轮毂附面层损失的减小不足以抵消叶顶附近所增加的损失,从而引起风机总损失增加,效率降低,噪声增大,其应用效果明显不如前弯。弯掠叶片内部流场的数值模拟结果进一步揭示了叶片弯掠后对内部流动参数分布的影响。在理论方面,通过改进损失计算模型和建立出口气流角与升力系数、总损失系数间的修正关系,进一步完善了弯掠叶片“双激盘”气动计算模型。通过对周向弯曲方向和弯曲角度的优化表明,动叶采用前弯技术明显优于后弯,动叶后弯后气动效率随弯曲角度的增大而明显降低；前弯动叶存在一最佳角度范围,主要取决于动叶前弯后上半叶高叶顶处损失的减小与叶片中部、下半叶高损失增加之间的平衡,合适的前弯角度可使叶片前弯后减小总损失,提高气动效率,本文中最佳前弯角度范围在2°～4°(对应叶顶处弯角6.5°～14.2°)为宜,此时风机效率可比径向叶片提高1.5%～2.0%。
4.可逆式组合叶片及弯掠组合叶片的研究
本文在现有T35原型叶片的基础上将叶片正反向组合后构成可逆式组合叶片。实验结果表明组合叶片可满足风机直接反转可逆式反风要求,且可保证正反向气动性能完全一致；后排反向叶片的加入在前、后排叶片间形成的加速流道有效改善了前列正向叶片吸力面附面层流动,但反向布置的后排叶片由于常规的平板圆弧叶型曲率方向与正常情况相反,后排叶片产生负压升,恶化了组合叶片的总体气动-声学性能；在组合叶片上引入弯掠技术形成弯掠组合叶片后,叶片径向力有效的减小了叶顶通道二次流和端壁附面层损失,总体气动-声学性能有大幅度提高,其中风机流量系数增加7.97%,全压系数增加9.69%,静压系数增加5.88%,效率增加11.78%,比A声级降低4.97dB,显示出良好的应用前景。
5.进一步工作展望
通过对本文的研究工作进行总结,结合目前风扇/压气机领域的研究动向,提出了弯掠叶片、组合叶片和弯掠组合叶片的进一步研究思路。
Reversible ventilation is crucial to the security of mines and tunnels. The inverse ventilation of axial flow fan by simply reverse motor has been proved excellent in the inverse ventilation fields. Designing axial flow turbomachinery such as fans, propellers, propfans, and compressors with skewed blades has several advantages. The noise emission is mostly lower and the aerodynamic performance can be widely improved. In this paper, detailed experimental and computational investigation has been carried on to a reversible fan with combined blades and two other fans with skewed blades. After that, a new-type reversible axial flow fan with skewed and combined blades is firstly invented.
Detail contents are listed as bellows,
1. Impeller design
In this paper, four different impellers, namely forward skewed impeller, backward skewed impeller, reversible combined impeller, and reversible combined&skewed impeller respectively, are designed and investigated. So far, to the best of our knowledge, no design method of skewed blade is available. This paper has developed a reverse engineering design (RED) process of skewed blade. In order to apply the optimal circumferential combine parameters from plain cascade experiment to actual impeller designation, a non-dimensional coefficient named relative pitch T'is defined and used as a criterion of combine parameters.
2. The test rig and measurement method
An aerodynamic&aeroacoustic test rig is designed and constructed in this thesis. Five hole probe and hot-wire (CTA) is employed to measure the three-dimensional velocity and pressure distribution downstream of each impeller. A rotating single slanted hot-wire technique and a periodic multi-sampling measurement system has been developed, with the use of a infrared probe as pulse generator. Typical experimental results of different rotating times and mass-average times are presented to investigate the measurement accuracy.
3. Study on the impellers with skewed blades
Experimental and computational results show that the aerodynamic and aeroacoustic perfonnance of the impellers with skewed blades can be widely influenced due to the transformation of passage vortex and the movement of low energy fluids in blade boudery layer. Performance of impeller with forward skewed blades is improved because of the lower passage vortex loss and the weaken boundary layer thickness at the impeller tip region. On the contrary, performances of impeller with backward skewed blades become worsen. Numerical flow simulation results give some details on the distributions of fluid field parameters. In the theory aspect, the so called Diactuator Disc Theory (DDT) is finally consummated and adopted to optimize the skew angle. It shows that appropriate forward skew angle may decrease the total pressure loss, improve aerodynamic efficiency, lower the aerodynamic noise, and enlarge the steady flow range. In this paper, impeller with forward-skew angle from2to4degree may get the best performance. The efficiency may be improved by1.5%-2.0%compared to impeller with straight blades.
4. Study on the reversible impellers with combined and skewed blades
First, a so called combined-impeller is investigated, which is composed of two rows of T35archetype blades, namely normal and reverse blades respectively. It shows the merits of fully reversible ventilation and direct re-rotating. However, the aerodynamic and aeroacoustic performance is not satisfied due to the negative pressure induced by the reverse blade. With the use of skewed blade technique, the new type reversible impeller with combined and skewed blades shows a great performance improvement. The flow rate coefficient is increased of7.97%, the total pressure coefficient is increased of9.69%, the static pressure coefficient is increased of5.88%, the efficiency is increased of11.78%, and the sound pressure level is decreased of4.97dB.
5. Conclusion and expectation
At the end of this thesis, research conclusions are presented and farther research expectations on skewed blade technique and the combined blade technique is also listed for reference.
本文以直接反转可逆式通风和弯掠叶片技术为研究对象,采用实验、理论和数值模拟等研究手段,首先研究了一种具有直接反转特点完全可逆式组合叶片的轴流风机。其次,在国内首次对具有相同几何参数和弯角大小的周向前弯和周向后弯动叶轮进行了对比研究,探讨了弯掠叶片的气动-声学特性及其内部流动机理,并进一步完善了适用于弯掠叶片气动计算的“双激盘”理论模型。最后,通过将弯掠叶片技术与组合叶片相结合,首次提出并研究了一种新型弯掠组合叶片。本文的主要研究工作包括：
1.叶轮设计
本文以目前工业通风领域广泛采用的T35型轴流风机作为设计原型,分别设计制造了周向前弯叶轮、周向后弯叶轮、可逆式组合叶轮和可逆式弯掠组合叶轮等四个叶轮。由于目前弯掠叶片领域尚未建立一套成熟的设计体系,本文首次尝试将逆向工程设计方法应用于弯掠叶片设计领域,建立了一套弯掠叶片逆向工程设计流程；此外,考虑到叶栅稠度沿叶高的变化,引入相对栅距系数T'作为叶片周向最佳组合参数的衡量指标,通过多方案分析成功将平面叶栅实验优化结果应用于可逆式组合叶片和弯掠组合叶片的设计。
2.实验装置及测试方法
本文建立了一套风机气动-声学实验装置。采用五孔探针和热线风速仪(CTA)对实验风机出口流场进行了详细测量,探讨了旋转单斜丝热线测量叶轮机械出口三维平均流场的方法,通过采用反射式红外跟踪触发系统,实现了同步触发多点采样平均技术在本文热线测试工作中的应用,通过分析热线单丝斜探头旋转次数和测量时测量数据总体平均次数对测试结果的影响,为热线的准确测量提供了依据。实验结果表明,本文所采用的实验装置和测试方法满足风机总体气动-声学性能及风机出口详细流场测量的要求。
3.弯掠叶片的理论与实验研究
弯掠动叶的径向力分量可有效控制通道内部径向压力梯度和叶片表面附面层中低能流体的流动,应用前弯技术有助于减小叶顶处通道二次流损失、减薄叶片表面附面层厚度、减少附面层内低能流体向叶顶处的堆积,极大改善了叶顶流动状况,有助于提高风机总体气动-声学性能；动叶后弯引起叶片下半叶高附面层内低能流体向叶片顶部迁移,增加了叶顶部分通道二次流和端壁损失,而下半叶高通道二次流损失和轮毂附面层损失的减小不足以抵消叶顶附近所增加的损失,从而引起风机总损失增加,效率降低,噪声增大,其应用效果明显不如前弯。弯掠叶片内部流场的数值模拟结果进一步揭示了叶片弯掠后对内部流动参数分布的影响。在理论方面,通过改进损失计算模型和建立出口气流角与升力系数、总损失系数间的修正关系,进一步完善了弯掠叶片“双激盘”气动计算模型。通过对周向弯曲方向和弯曲角度的优化表明,动叶采用前弯技术明显优于后弯,动叶后弯后气动效率随弯曲角度的增大而明显降低；前弯动叶存在一最佳角度范围,主要取决于动叶前弯后上半叶高叶顶处损失的减小与叶片中部、下半叶高损失增加之间的平衡,合适的前弯角度可使叶片前弯后减小总损失,提高气动效率,本文中最佳前弯角度范围在2°～4°(对应叶顶处弯角6.5°～14.2°)为宜,此时风机效率可比径向叶片提高1.5%～2.0%。
4.可逆式组合叶片及弯掠组合叶片的研究
本文在现有T35原型叶片的基础上将叶片正反向组合后构成可逆式组合叶片。实验结果表明组合叶片可满足风机直接反转可逆式反风要求,且可保证正反向气动性能完全一致；后排反向叶片的加入在前、后排叶片间形成的加速流道有效改善了前列正向叶片吸力面附面层流动,但反向布置的后排叶片由于常规的平板圆弧叶型曲率方向与正常情况相反,后排叶片产生负压升,恶化了组合叶片的总体气动-声学性能；在组合叶片上引入弯掠技术形成弯掠组合叶片后,叶片径向力有效的减小了叶顶通道二次流和端壁附面层损失,总体气动-声学性能有大幅度提高,其中风机流量系数增加7.97%,全压系数增加9.69%,静压系数增加5.88%,效率增加11.78%,比A声级降低4.97dB,显示出良好的应用前景。
5.进一步工作展望
通过对本文的研究工作进行总结,结合目前风扇/压气机领域的研究动向,提出了弯掠叶片、组合叶片和弯掠组合叶片的进一步研究思路。
Reversible ventilation is crucial to the security of mines and tunnels. The inverse ventilation of axial flow fan by simply reverse motor has been proved excellent in the inverse ventilation fields. Designing axial flow turbomachinery such as fans, propellers, propfans, and compressors with skewed blades has several advantages. The noise emission is mostly lower and the aerodynamic performance can be widely improved. In this paper, detailed experimental and computational investigation has been carried on to a reversible fan with combined blades and two other fans with skewed blades. After that, a new-type reversible axial flow fan with skewed and combined blades is firstly invented.
Detail contents are listed as bellows,
1. Impeller design
In this paper, four different impellers, namely forward skewed impeller, backward skewed impeller, reversible combined impeller, and reversible combined&skewed impeller respectively, are designed and investigated. So far, to the best of our knowledge, no design method of skewed blade is available. This paper has developed a reverse engineering design (RED) process of skewed blade. In order to apply the optimal circumferential combine parameters from plain cascade experiment to actual impeller designation, a non-dimensional coefficient named relative pitch T'is defined and used as a criterion of combine parameters.
2. The test rig and measurement method
An aerodynamic&aeroacoustic test rig is designed and constructed in this thesis. Five hole probe and hot-wire (CTA) is employed to measure the three-dimensional velocity and pressure distribution downstream of each impeller. A rotating single slanted hot-wire technique and a periodic multi-sampling measurement system has been developed, with the use of a infrared probe as pulse generator. Typical experimental results of different rotating times and mass-average times are presented to investigate the measurement accuracy.
3. Study on the impellers with skewed blades
Experimental and computational results show that the aerodynamic and aeroacoustic perfonnance of the impellers with skewed blades can be widely influenced due to the transformation of passage vortex and the movement of low energy fluids in blade boudery layer. Performance of impeller with forward skewed blades is improved because of the lower passage vortex loss and the weaken boundary layer thickness at the impeller tip region. On the contrary, performances of impeller with backward skewed blades become worsen. Numerical flow simulation results give some details on the distributions of fluid field parameters. In the theory aspect, the so called Diactuator Disc Theory (DDT) is finally consummated and adopted to optimize the skew angle. It shows that appropriate forward skew angle may decrease the total pressure loss, improve aerodynamic efficiency, lower the aerodynamic noise, and enlarge the steady flow range. In this paper, impeller with forward-skew angle from2to4degree may get the best performance. The efficiency may be improved by1.5%-2.0%compared to impeller with straight blades.
4. Study on the reversible impellers with combined and skewed blades
First, a so called combined-impeller is investigated, which is composed of two rows of T35archetype blades, namely normal and reverse blades respectively. It shows the merits of fully reversible ventilation and direct re-rotating. However, the aerodynamic and aeroacoustic performance is not satisfied due to the negative pressure induced by the reverse blade. With the use of skewed blade technique, the new type reversible impeller with combined and skewed blades shows a great performance improvement. The flow rate coefficient is increased of7.97%, the total pressure coefficient is increased of9.69%, the static pressure coefficient is increased of5.88%, the efficiency is increased of11.78%, and the sound pressure level is decreased of4.97dB.
5. Conclusion and expectation
At the end of this thesis, research conclusions are presented and farther research expectations on skewed blade technique and the combined blade technique is also listed for reference.
引文
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