跨音速高压涡轮转子叶尖间隙泄漏流动及控制方法研究
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摘要
涡轮转子叶尖间隙泄漏流动导致间隙附近损失增加，涡轮效率下降。为降低间隙泄漏损失提高涡轮效率，本文以某跨音速高压高负荷涡轮为研究对象，在间隙泄漏流动机理研究的基础上开展间隙泄漏流动控制研究，并进一步研究间隙泄漏流动控制对发动机性能的影响。
首先，利用三维CFD数值模拟方法对间隙泄漏流动进行研究，分析间隙泄漏流动结构以及间隙泄漏损失的来源及分布规律，并探讨间隙高度、转速等参数对间隙泄漏流动的影响。同时对间隙泄漏流动的非定常性开展研究，分析间隙泄漏流动的非定常特征及其成因。
然后进行间隙泄漏流动控制研究。首先研究转子叶尖增加翼梢小翼对间隙泄漏流动的影响，结果发现吸力边翼梢小翼一定程度上隔离了间隙泄漏流和泄漏涡，有效地抑制泄漏涡的生成和发展，减小了泄漏损失；同时吸力边小翼削弱了叶片吸力面壁面潜流的强度，减小壁面二次流动损失，提高了涡轮效率。在间隙泄漏流动控制研究基础上，对翼梢小翼形状和位置进行改进，设计出一种新型翼梢小翼，可以使间隙泄漏损失进一步降低，使涡轮效率提高0.42%。
同时对叶尖肋条的影响进行研究，结果表明在叶顶增加全周肋条/叶顶凹槽的效果优于单边肋条。叶顶凹槽内的漩涡阻碍泄漏流体通过间隙，导致间隙泄漏流量降低；叶顶凹槽还将泄漏流体向间隙后部输运，导致间隙吸力面30%至60%弦长范围内的泄漏流量明显降低，泄漏涡强度减弱，间隙泄漏损失减小。研究发现对叶顶凹槽形状进行改进可以提高凹槽的控制效果，使泄漏损失进一步降低。本文设计一种新型的叶顶凹槽结构，可以使涡轮效率增加0.36%。
最后，建立了一个考虑涡轮转子叶尖间隙高度变化的发动机性能仿真模型，该模型可以计算涡轮转子叶尖间隙高度，并将间隙高度变化情况反馈至间隙泄漏流动控制结果，使涡轮性能随之变化，进而求得间隙泄漏流动对发动机性能的影响。利用文中建立的模型对翼梢小翼和叶顶凹槽对发动机性能的影响进行研究。结果发现间隙泄漏流动控制导致发动机耗油率降低，提高了发动机的经济性。从整个飞行包线来看，叶顶凹槽对发动机性能的提升优于翼梢小翼。
Tip clearance leakage flow leads to remarkable losses near the tip clearance, whichresults in the decrease of the aerodynamic and thermal performance of the high pressureturbine. In order to reduce the tip leakage loss and increase the efficiency of the turbinestage, a transonic high pressure turbine was researched. Based on the mechanismstudies of the tip leakage flow, tip desensitization was studied, and the influence onengine performance of tip desensitization was also investigated.
Firstly, numerical simulations of the structure of the tip clearance and the genesisof tip leakage loss were emphasized by resolving three dimensional Navier-Stokesequations, and the influences of the height of the tip clearance was considered as well asthe rotation speed. The unsteady characteristic of the tip leakage flow and their genesiswere also studied by three dimensional unsteady simulations.
Then, tip desensitization was researched. The influence of tip winglets on the tipclearance leakage flow was firstly investigated. Results show that the suction-sidewinglets divide the tip leakage flow and the leakage vortex, which weakens the leakagevortex as well as the underflow on the suction side of the rotor blade. As a result, thelosses decrease markedly and the efficiency of the turbine increases. Based on thestudies, a new winglet was designed. The new winglet further lessens the tip leakageloss, and the turbine efficiency improves by0.42%.
The influence of squealer rims was studied too. The study indicates that theinfluence of the double side squealer rims is better than single squealer rim. Thevortexes in the basin block the tip leakage flow passes through the tip clearance, and thetip leakage flow mass reduces markedly as a result. The basin also transports the tipleakage flow from the leading edge to the trailing edge of the tip clearance, resulting inthe decrease of tip leakage flow mass in30%to60%chord length. The strength of theleakage vortex weakens and the tip leakage loss reduces. A well-designed tip basin waspresented in this paper, which leads to the turbine efficiency improves by0.36%.
Finally, a tip-clearance-height-considered propulsion simulation model wasestablished. The model can calculate the clearance height, and send the change of the tipclearance height back to the tip desensitization, which makes the turbine efficiency changes, and then the influence of tip desensitization be achieved. The influence onengine performances of tip desensitization such as tip winglets and tip cavities werestudied, and the result shows that tip desensitization leads to the decrease of specificfuel consumption, the economical efficiency of engines is improved. In most ways thetip cavities improve engine performances better than tip winglets.
首先，利用三维CFD数值模拟方法对间隙泄漏流动进行研究，分析间隙泄漏流动结构以及间隙泄漏损失的来源及分布规律，并探讨间隙高度、转速等参数对间隙泄漏流动的影响。同时对间隙泄漏流动的非定常性开展研究，分析间隙泄漏流动的非定常特征及其成因。
然后进行间隙泄漏流动控制研究。首先研究转子叶尖增加翼梢小翼对间隙泄漏流动的影响，结果发现吸力边翼梢小翼一定程度上隔离了间隙泄漏流和泄漏涡，有效地抑制泄漏涡的生成和发展，减小了泄漏损失；同时吸力边小翼削弱了叶片吸力面壁面潜流的强度，减小壁面二次流动损失，提高了涡轮效率。在间隙泄漏流动控制研究基础上，对翼梢小翼形状和位置进行改进，设计出一种新型翼梢小翼，可以使间隙泄漏损失进一步降低，使涡轮效率提高0.42%。
同时对叶尖肋条的影响进行研究，结果表明在叶顶增加全周肋条/叶顶凹槽的效果优于单边肋条。叶顶凹槽内的漩涡阻碍泄漏流体通过间隙，导致间隙泄漏流量降低；叶顶凹槽还将泄漏流体向间隙后部输运，导致间隙吸力面30%至60%弦长范围内的泄漏流量明显降低，泄漏涡强度减弱，间隙泄漏损失减小。研究发现对叶顶凹槽形状进行改进可以提高凹槽的控制效果，使泄漏损失进一步降低。本文设计一种新型的叶顶凹槽结构，可以使涡轮效率增加0.36%。
最后，建立了一个考虑涡轮转子叶尖间隙高度变化的发动机性能仿真模型，该模型可以计算涡轮转子叶尖间隙高度，并将间隙高度变化情况反馈至间隙泄漏流动控制结果，使涡轮性能随之变化，进而求得间隙泄漏流动对发动机性能的影响。利用文中建立的模型对翼梢小翼和叶顶凹槽对发动机性能的影响进行研究。结果发现间隙泄漏流动控制导致发动机耗油率降低，提高了发动机的经济性。从整个飞行包线来看，叶顶凹槽对发动机性能的提升优于翼梢小翼。
Tip clearance leakage flow leads to remarkable losses near the tip clearance, whichresults in the decrease of the aerodynamic and thermal performance of the high pressureturbine. In order to reduce the tip leakage loss and increase the efficiency of the turbinestage, a transonic high pressure turbine was researched. Based on the mechanismstudies of the tip leakage flow, tip desensitization was studied, and the influence onengine performance of tip desensitization was also investigated.
Firstly, numerical simulations of the structure of the tip clearance and the genesisof tip leakage loss were emphasized by resolving three dimensional Navier-Stokesequations, and the influences of the height of the tip clearance was considered as well asthe rotation speed. The unsteady characteristic of the tip leakage flow and their genesiswere also studied by three dimensional unsteady simulations.
Then, tip desensitization was researched. The influence of tip winglets on the tipclearance leakage flow was firstly investigated. Results show that the suction-sidewinglets divide the tip leakage flow and the leakage vortex, which weakens the leakagevortex as well as the underflow on the suction side of the rotor blade. As a result, thelosses decrease markedly and the efficiency of the turbine increases. Based on thestudies, a new winglet was designed. The new winglet further lessens the tip leakageloss, and the turbine efficiency improves by0.42%.
The influence of squealer rims was studied too. The study indicates that theinfluence of the double side squealer rims is better than single squealer rim. Thevortexes in the basin block the tip leakage flow passes through the tip clearance, and thetip leakage flow mass reduces markedly as a result. The basin also transports the tipleakage flow from the leading edge to the trailing edge of the tip clearance, resulting inthe decrease of tip leakage flow mass in30%to60%chord length. The strength of theleakage vortex weakens and the tip leakage loss reduces. A well-designed tip basin waspresented in this paper, which leads to the turbine efficiency improves by0.36%.
Finally, a tip-clearance-height-considered propulsion simulation model wasestablished. The model can calculate the clearance height, and send the change of the tipclearance height back to the tip desensitization, which makes the turbine efficiency changes, and then the influence of tip desensitization be achieved. The influence onengine performances of tip desensitization such as tip winglets and tip cavities werestudied, and the result shows that tip desensitization leads to the decrease of specificfuel consumption, the economical efficiency of engines is improved. In most ways thetip cavities improve engine performances better than tip winglets.
引文
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