前缘弯掠（扭）斜流转子内流机制的数值分析及实验研究
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摘要
弯掠叶片的成型方法自六十年代初提出以来,受到世界各国研究人员的高度重视。随着相关学科的发展,弯掠叶片成型规律的研究逐渐形成了“弯掠叶片动力学”分支学科。合理运用弯掠能够改变叶轮机械的静压梯度分布、抑制二次流发展和端壁低能流体的聚集,达到提高气动性能的目的。为此,本文设计和研制了前缘弯掠(扭)斜流转子,并对其内流机制进行了数值分析和实验研究,探索弯掠设计和实验研究对提高风扇/压气机失速裕度的有效途径。
文中详细给出了基于假想等价速度三角形和1/7边界层法则的前缘弯掠(扭)斜流转子的准三元设计方法,以及为保持叶栅性能不变的Schlichting理论修正公式和修正方法,编写了设计计算程序。本文设计的前缘弯掠(扭)斜流转子的主要特点是:转子叶片顶部和叶片根部前缘弯掠(扭),叶片中弧线保持不变,即叶片出口气流角与常规叶片相同,因此可以在不变更常规设计系统条件下进行前缘弯掠设计。
文中自行设计并研制了前缘弯掠(扭)斜流转子,在自行设计和集成制造的(符合AMCA210-85,GB1236-2000标准)全自动风机外特性实验台上进行的气动特性测试结果表明,前缘弯掠(扭)斜流转子消除了常规斜流转子在低流量时的失速区域,扩大了运行工况范围。前缘弯掠(扭)斜流转子的计算结果和性能实验结果吻合。
研究并数值分析了前缘弯掠(扭)斜流转子内部复杂的流动现象,揭示了前缘弯掠(扭)斜流转子内的流动机制;即前缘弯掠(扭)斜流转子消除了常规斜流转子吸力面叶根前缘存在的回流,将端壁区域的低能流体吸收到叶片中部高能主流中,减弱了端部低能流体的聚集,从而减弱了流动损失和流动阻塞。计算结果的比较表明,前缘弯掠(扭)斜流转子的叶片尾迹比常规斜流转子弱,机壳和轮毂端壁对转子尾迹的影响减弱,抑制了低能流体的堆积,扩大了运行工况范围。
文中数值分析了前缘弯掠(扭)斜流转子叶顶间隙泄漏涡在不同间隙时的流动机制。研究发现:大间隙时,叶顶间隙泄漏流与主流发生了强烈的卷吸;叶顶泄漏涡产生于弦长33%的轴向位置,靠近吸力面,泄漏涡沿着与转子旋向相反的方向朝相邻叶片的压力面向下游发展。叶顶间隙增加时,泄漏涡增强。当流量减小时,叶顶泄漏涡
国家自然科学基金项目No: 50176012;教育部博士学科点专项基金项目No: 20020487025
的作用区域扩大,损失增加,间隙泄漏流与主流的卷吸作用更加强烈。
本文应用PIV技术首次对前缘弯掠(扭)开式斜流转子的叶尖涡流动特性进行了测量并与CFD结果作了比较。PIV测量结果表明,叶尖涡是由沿子午面流动的主气流与从叶顶外侧吸入的气流相互卷吸而产生,叶尖涡产生于叶片吸力面近叶顶区域,大致沿着一条与叶轮旋转方向相反的斜线向转子下游发展,持续到转子叶顶出口下游65%弦长位置。叶尖脱落涡的强度及其卷吸区域随叶轮转速的提高而增强,随背压的提高而减弱,当背压增加到一定程度时,叶尖脱落涡消失。实验结果和计算结果吻合,验证了本文计算方法的妥当性和PIV实验结果的可靠性。
Since the molding methods of the skewed-swept blade were proposed from 1960’s, the Researches from all over the world attach high importance to it. With the development of the related subjects, the Research on the skewed-swept blade-molding rule gradually develop into a subject of “sweep aerodynamics”. It can change the static pressure grads distribution; restrain the development of the secondary flow; reduce the conglomeration of the low-momentum fluid near the wall region and improve the aerodynamic characteristic of the turbomachinery by sweeping and skewing the blade properly. In order to explore the effective approach of improving the stall margin of fans and compressors by sweeping and skewing the rotor, the leading edge skewed-swept diagonal rotor is designed and studied, its internal flow mechanism is analyzed by numerical simulation and experimental research in this dissertation.
The quasi-three-dimensional design method of the leading edge skewed-swept diagonal rotor is given in detail. This design method is based on the virtual-equivalent velocity triangle diagram and the one-seventh boundary layer rule. In order to keep the blade cascade characteristic is the same with the practical data, the theoretical correcting equations and methods, which was originally proposed by Schlichting, is also given. The computer software is programmed to design the leading edge skewed-swept diagonal rotor in this dissertation. The designed skewed-swept diagonal rotor has the following distinctive features: The leading edge is skewed and swept near the hub and casing wall region. The blade’s camber line is the same as the conventional rotor; that is to say, the rotor’s exit flow angle is the same as the conventional rotor. So the leading edge skewed-swept diagonal rotor can be designed under the conventional design system.
The leading edge skewed-swept diagonal rotor is designed. Its aerodynamic characteristic curve is measured on the own-made automatic testing equipment that was designed according to the AMCA210-85 and GB1236-2000 standards. The tested results show that the skewed-swept diagonal rotor diminished the stall region that was usually existed at the lower flow rate for the normal diagonal rotor. The newly designed diagonal rotor increased the working range. The calculated characteristic curve of the skewed-swept
It is supported by the National Natural Science Foundation of China (No: 50176012 ) and the Doctorate Foundation of the Ministry of Education(No: 20020487025)
diagonal rotor is in good agreement with the tested data.
The complex internal flow phenomena of the leading edge skewed-swept diagonal rotor are calculated and analyzed by using commercial CFD software. The internal flow mechanism of the skewed-swept diagonal rotor is revealed. The backflow that existed at the suction surface near the leading edge and hub wall region of the normal diagonal rotor is eliminated by the leading edge skew and sweep. The low energy fluid near the hub wall region is sucked into the high-energy fluid near the blade’s middle region. The conglomeration of low energy near the hub wall region is reduced. The fluid block and loss is decreased. The calculated results showed that, the wake of the skewed-swept diagonal is weaker than that of the normal diagonal rotor; the influence of the casing and hub wall on the wake is weakened; the blockage of the low energy fluid near the hub wall region is reduced and the working range of the leading edge skewed-swept diagonal rotor is increased.
The leakage vortex and the tip clearance flow mechanism is revealed and discussed at different clearance size and different flow rate by using CFD simulation. At large tip clearance size, there exists the strong rolling up of the fluid between the clearance flow and the main flow. The leakage vortex is generated at the axial position of 33% chord length of the blade tip, and it is near the blade’s suction surface. The leakage vortex moves toward the adjacent blade’s pressure surface in the blade’s flow passage along the rever
文中详细给出了基于假想等价速度三角形和1/7边界层法则的前缘弯掠(扭)斜流转子的准三元设计方法,以及为保持叶栅性能不变的Schlichting理论修正公式和修正方法,编写了设计计算程序。本文设计的前缘弯掠(扭)斜流转子的主要特点是:转子叶片顶部和叶片根部前缘弯掠(扭),叶片中弧线保持不变,即叶片出口气流角与常规叶片相同,因此可以在不变更常规设计系统条件下进行前缘弯掠设计。
文中自行设计并研制了前缘弯掠(扭)斜流转子,在自行设计和集成制造的(符合AMCA210-85,GB1236-2000标准)全自动风机外特性实验台上进行的气动特性测试结果表明,前缘弯掠(扭)斜流转子消除了常规斜流转子在低流量时的失速区域,扩大了运行工况范围。前缘弯掠(扭)斜流转子的计算结果和性能实验结果吻合。
研究并数值分析了前缘弯掠(扭)斜流转子内部复杂的流动现象,揭示了前缘弯掠(扭)斜流转子内的流动机制;即前缘弯掠(扭)斜流转子消除了常规斜流转子吸力面叶根前缘存在的回流,将端壁区域的低能流体吸收到叶片中部高能主流中,减弱了端部低能流体的聚集,从而减弱了流动损失和流动阻塞。计算结果的比较表明,前缘弯掠(扭)斜流转子的叶片尾迹比常规斜流转子弱,机壳和轮毂端壁对转子尾迹的影响减弱,抑制了低能流体的堆积,扩大了运行工况范围。
文中数值分析了前缘弯掠(扭)斜流转子叶顶间隙泄漏涡在不同间隙时的流动机制。研究发现:大间隙时,叶顶间隙泄漏流与主流发生了强烈的卷吸;叶顶泄漏涡产生于弦长33%的轴向位置,靠近吸力面,泄漏涡沿着与转子旋向相反的方向朝相邻叶片的压力面向下游发展。叶顶间隙增加时,泄漏涡增强。当流量减小时,叶顶泄漏涡
国家自然科学基金项目No: 50176012;教育部博士学科点专项基金项目No: 20020487025
的作用区域扩大,损失增加,间隙泄漏流与主流的卷吸作用更加强烈。
本文应用PIV技术首次对前缘弯掠(扭)开式斜流转子的叶尖涡流动特性进行了测量并与CFD结果作了比较。PIV测量结果表明,叶尖涡是由沿子午面流动的主气流与从叶顶外侧吸入的气流相互卷吸而产生,叶尖涡产生于叶片吸力面近叶顶区域,大致沿着一条与叶轮旋转方向相反的斜线向转子下游发展,持续到转子叶顶出口下游65%弦长位置。叶尖脱落涡的强度及其卷吸区域随叶轮转速的提高而增强,随背压的提高而减弱,当背压增加到一定程度时,叶尖脱落涡消失。实验结果和计算结果吻合,验证了本文计算方法的妥当性和PIV实验结果的可靠性。
Since the molding methods of the skewed-swept blade were proposed from 1960’s, the Researches from all over the world attach high importance to it. With the development of the related subjects, the Research on the skewed-swept blade-molding rule gradually develop into a subject of “sweep aerodynamics”. It can change the static pressure grads distribution; restrain the development of the secondary flow; reduce the conglomeration of the low-momentum fluid near the wall region and improve the aerodynamic characteristic of the turbomachinery by sweeping and skewing the blade properly. In order to explore the effective approach of improving the stall margin of fans and compressors by sweeping and skewing the rotor, the leading edge skewed-swept diagonal rotor is designed and studied, its internal flow mechanism is analyzed by numerical simulation and experimental research in this dissertation.
The quasi-three-dimensional design method of the leading edge skewed-swept diagonal rotor is given in detail. This design method is based on the virtual-equivalent velocity triangle diagram and the one-seventh boundary layer rule. In order to keep the blade cascade characteristic is the same with the practical data, the theoretical correcting equations and methods, which was originally proposed by Schlichting, is also given. The computer software is programmed to design the leading edge skewed-swept diagonal rotor in this dissertation. The designed skewed-swept diagonal rotor has the following distinctive features: The leading edge is skewed and swept near the hub and casing wall region. The blade’s camber line is the same as the conventional rotor; that is to say, the rotor’s exit flow angle is the same as the conventional rotor. So the leading edge skewed-swept diagonal rotor can be designed under the conventional design system.
The leading edge skewed-swept diagonal rotor is designed. Its aerodynamic characteristic curve is measured on the own-made automatic testing equipment that was designed according to the AMCA210-85 and GB1236-2000 standards. The tested results show that the skewed-swept diagonal rotor diminished the stall region that was usually existed at the lower flow rate for the normal diagonal rotor. The newly designed diagonal rotor increased the working range. The calculated characteristic curve of the skewed-swept
It is supported by the National Natural Science Foundation of China (No: 50176012 ) and the Doctorate Foundation of the Ministry of Education(No: 20020487025)
diagonal rotor is in good agreement with the tested data.
The complex internal flow phenomena of the leading edge skewed-swept diagonal rotor are calculated and analyzed by using commercial CFD software. The internal flow mechanism of the skewed-swept diagonal rotor is revealed. The backflow that existed at the suction surface near the leading edge and hub wall region of the normal diagonal rotor is eliminated by the leading edge skew and sweep. The low energy fluid near the hub wall region is sucked into the high-energy fluid near the blade’s middle region. The conglomeration of low energy near the hub wall region is reduced. The fluid block and loss is decreased. The calculated results showed that, the wake of the skewed-swept diagonal is weaker than that of the normal diagonal rotor; the influence of the casing and hub wall on the wake is weakened; the blockage of the low energy fluid near the hub wall region is reduced and the working range of the leading edge skewed-swept diagonal rotor is increased.
The leakage vortex and the tip clearance flow mechanism is revealed and discussed at different clearance size and different flow rate by using CFD simulation. At large tip clearance size, there exists the strong rolling up of the fluid between the clearance flow and the main flow. The leakage vortex is generated at the axial position of 33% chord length of the blade tip, and it is near the blade’s suction surface. The leakage vortex moves toward the adjacent blade’s pressure surface in the blade’s flow passage along the rever
引文
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