D型涡扇发动机风扇改型设计研究
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摘要
传统的准三维设计方法曾经设计出大量性能优良的叶轮机械,并且一维和准三维设计方法由于其丰富的设计经验,至今仍然在叶轮机械的设计中发挥重要的作用。但在现代风扇/压气机向高通流、高负荷、高效率的方向发展时基于传统准三维设计体系的设计方法就暴露出它的局限性和不足。基于上述原因本文系统地总结了风扇/压气机设计技术体系的发展概况,改进了传统的准三维设计体系,建立了一个适用于现代风扇/压气机的设计体系。该设计技术体系既继承了传统的设计经验,又有新的设计技术的加入,它适合于我国当前风扇/压气机设计计算能力。本文还对该设计体系的基本原理和工作流程作了简明扼要的总结。
为了解决风扇/压气机设计中经常遇到的叶片表面流场分离问题,本文以轴对称流动作为主流,对叶轮机械的二次流动问题进行了深入地研究。根据轴对称流的主控制方程中各项的含义,研究了影响主方程平衡关系的三个因素,即流线曲率、气体绕压气机轴线旋转产生的惯性离心力和叶片力。根据这三个因素提出了弯曲静子叶片设计的气动正交准则,该方法对提高喘振裕度和非设计点性能有较好效果。采用气动正交的设计方法是本设计体系的一个重要特色。
本文采用该设计体系对D型发动机的风扇转子叶片进行了改型设计,全三维流场计算结果表明风扇性能达到了设计指标。为了解决第一排静子叶片叶尖和轮毂部分的分离,采用了气动正交的方法对该静子叶片进行了重新设计,基本消除了叶尖和轮毂部分的分离,风扇级的非设计点性能和喘振裕度有较大提高。
本文还介绍了基于伴随方法的全三维流场优化方法,采用Rotor 67转子验证了该方法的有效性,然后利用该方法对改型风扇转子叶片进行了全三维流场优化,优化后的风扇转子比优化前效率提高了2%。优化结果表明基于伴随方法的全三维流场优化是高性能风扇/压气机设计体系的一个重要组成部分。
本文最后对设计点转速为25850rpm的改型风扇转子进行了部件试验和整机验证试验,试验结果表明本文采用的压气机气动设计方法是可行的,该改型风扇转子可以用于D型发动机的改型。
Many turbomachineries with super performance has been designed with the aid of traditional quasi-three-dimensional design method, which still play a important role in modern turbomachinery design process, and a lot of design experience has been established. However, for the tendency of High throughflow, High load and High efficiency (3H) turbomachinery, traditional design system starts to show its deficiency. In this dissertation, first, a review on development of fan/compressor design technique has been made; then, based on the traditional design system, a elementary modern fan/compressor design system, which is well suited to the domestic computational capacity now, has been constructed, by including some new design concept. Also, the basic principle and flowchart of aerodynamic process is reviewed briefly.
Considering the flow separation, which is frequently met in fan/compressor design process, a deep analysis to the secondary flow in turbomachines is present based on the axis-symmetric inviscid governing equation, the analysis shows that there are three primary factors, which influence the force balance in flow passage. Based on this recognition, an new rule for bowed stator design --- Aero-Orthogonality (AO) rule is proposed here. Experience shows that the rule is very effective in improving surge margin and off-design performance.
With the help of the improved design system, a fan stage redesign is conducted, and 3-D flow field calculation verifies that the design object is satisfied. To eliminate flow separation at the tip and hub section, AO rule is applied and the result is satisfactory.
Also, A new optimization technique is adopted in the new design system --- Adjoint method, NASA rotor 67 is first redesigned by this method to show its potential of performance improvement, then this method is applied to the rotor of fan stage. The result is fairly encouraging. The rotor efficient get a 2% gain, which means that the adjoint method do improve the three dimensional flow fields, and is indispensable to the new design system.
Finally, experiment of the redesigned fan stage at the revolution 25850rpm is conducted, which vertifies that the design system used in this paper is feasible and the redesign work of the fan stage is successful.
为了解决风扇/压气机设计中经常遇到的叶片表面流场分离问题,本文以轴对称流动作为主流,对叶轮机械的二次流动问题进行了深入地研究。根据轴对称流的主控制方程中各项的含义,研究了影响主方程平衡关系的三个因素,即流线曲率、气体绕压气机轴线旋转产生的惯性离心力和叶片力。根据这三个因素提出了弯曲静子叶片设计的气动正交准则,该方法对提高喘振裕度和非设计点性能有较好效果。采用气动正交的设计方法是本设计体系的一个重要特色。
本文采用该设计体系对D型发动机的风扇转子叶片进行了改型设计,全三维流场计算结果表明风扇性能达到了设计指标。为了解决第一排静子叶片叶尖和轮毂部分的分离,采用了气动正交的方法对该静子叶片进行了重新设计,基本消除了叶尖和轮毂部分的分离,风扇级的非设计点性能和喘振裕度有较大提高。
本文还介绍了基于伴随方法的全三维流场优化方法,采用Rotor 67转子验证了该方法的有效性,然后利用该方法对改型风扇转子叶片进行了全三维流场优化,优化后的风扇转子比优化前效率提高了2%。优化结果表明基于伴随方法的全三维流场优化是高性能风扇/压气机设计体系的一个重要组成部分。
本文最后对设计点转速为25850rpm的改型风扇转子进行了部件试验和整机验证试验,试验结果表明本文采用的压气机气动设计方法是可行的,该改型风扇转子可以用于D型发动机的改型。
Many turbomachineries with super performance has been designed with the aid of traditional quasi-three-dimensional design method, which still play a important role in modern turbomachinery design process, and a lot of design experience has been established. However, for the tendency of High throughflow, High load and High efficiency (3H) turbomachinery, traditional design system starts to show its deficiency. In this dissertation, first, a review on development of fan/compressor design technique has been made; then, based on the traditional design system, a elementary modern fan/compressor design system, which is well suited to the domestic computational capacity now, has been constructed, by including some new design concept. Also, the basic principle and flowchart of aerodynamic process is reviewed briefly.
Considering the flow separation, which is frequently met in fan/compressor design process, a deep analysis to the secondary flow in turbomachines is present based on the axis-symmetric inviscid governing equation, the analysis shows that there are three primary factors, which influence the force balance in flow passage. Based on this recognition, an new rule for bowed stator design --- Aero-Orthogonality (AO) rule is proposed here. Experience shows that the rule is very effective in improving surge margin and off-design performance.
With the help of the improved design system, a fan stage redesign is conducted, and 3-D flow field calculation verifies that the design object is satisfied. To eliminate flow separation at the tip and hub section, AO rule is applied and the result is satisfactory.
Also, A new optimization technique is adopted in the new design system --- Adjoint method, NASA rotor 67 is first redesigned by this method to show its potential of performance improvement, then this method is applied to the rotor of fan stage. The result is fairly encouraging. The rotor efficient get a 2% gain, which means that the adjoint method do improve the three dimensional flow fields, and is indispensable to the new design system.
Finally, experiment of the redesigned fan stage at the revolution 25850rpm is conducted, which vertifies that the design system used in this paper is feasible and the redesign work of the fan stage is successful.
引文
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