对转涡轮气动优化设计及其热斑效应的研究
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摘要
鉴于对转涡轮技术在提高涡轮气动效率、降低涡轮端重量以及提高飞机机动性能等诸多方面的优势,欧美等航空强国将对转涡轮技术作为了重要的研究内容,并已将其成功地应用到了新一代军用与民用航空发动机之中。与之相比,我国在对转涡轮技术上的研究还颇为不足,对转涡轮气动设计及优化的经验尚有欠缺。此外,在常规涡轮中,研究者们已经发现了进口热斑会对涡轮的流场和热负荷产生不可忽视的影响,但迄今为止热斑对无导叶对转涡轮流场、气动性能以及热负荷的影响研究还非常少。鉴于此,本文在课题组已有研究成果的基础上,针对对转涡轮的气动优化设计及其热斑效应进行了研究,主要研究内容如下：
1.对某1+1对转涡轮进行了气动设计,并通过数值模拟的手段对其流场和气动性能进行了分析,总结出了相关设计特征。研究发现涡轮上端壁采用下凹型的曲线有利于降低叶顶反动度,低压级采用“反C”型出功分配将导致低压导叶出口气流角的径向差异较大。
2.研究了导叶弯曲对1+1/2对转涡轮气动性能的影响,重点研究了导叶在不同正弯角度和不同反弯角度下导叶通道内流场的变化,气流出口特性的变化以及高低压级涡轮等熵效率的变化,进而得到了导叶弯曲对1+1/2对转涡轮气动性能的影响方式及机理,并发现了导叶在小角度反弯时有利于1+1/2对转涡轮效率的提高。
3.通过对1+1/2对转涡轮在均匀温度进口工况和热斑工况下的定常/非定常数值模拟结果的比较,研究了进口热斑对1+1/2对转涡轮高低压两级转子通道内径向二次流以及涡强度的影响,发现了热斑的引入加剧了气流在高压转子通道内的径向二次流动,增强了高压转子根部通道涡和尾迹涡的强度,但降低了高压转子顶部泄漏涡的强度。还发现了在热斑的影响下,低压转子根部通道涡有所减弱。
4.开展了热斑对1+1/2对转涡轮叶表、叶顶以及端壁热负荷的影响研究,揭示了进口热斑与径向二次流以及顶部泄漏涡等相互作用对1+1/2对转涡轮热负荷的影响机理,发现了在热斑工况下高压转子叶顶尾部和低压转子叶顶尾部的热负荷因高温气体的掠过而增强,高压转子轮毂后端的热负荷和低压转子轮毂的热负荷因高温气体的径向迁移而增强,此外还发现了迁移至叶顶的高温流体在叶顶泄漏涡的卷吸下远离机匣,从而使得机匣的热负荷在热斑工况下有所下降。
5.研究了热斑的存在对1+1/2对转涡轮比功和等熵效率等气动性能的影响,发现了热斑工况下叶中高温流体出功增加,而两端低温流体出功降低；由于叶中高温流体在出功的同时还要向两端低温流体输送能量,因此叶中区域的等熵效率因热斑的引入而降低,两端区域的等熵效率因热斑的引入而升高。
Counter-Rotating turbine (CRT) can offer some significant benefits compared with conventional two-stage turbines, such as the elevated efficiency, the reduced weight, the improved performance of aircraft and so on. So, the aviation powers in Europe and America pay great attentions on the study of CRT, and the CRT has been succsfully applied in the military aero-engines and in the civil aero-engines in those countries. However, the recearch level of the CRT in China is very low, especially in the aerodynamic design and optimization. In addition, researchers have found that hot streak can affect the flow field and heat load in conventional turbines, but the study of the hot steak effects on the flow field, aerodynamic performance and heat load in the Vanless Counter-Rotating Turbine (VCRT) is very few. In view of this background, the investigations on the aerodynamic optimization design and hot steak effects in CRT are showed in this paper. The main content in this paper is listed as follows:
1. An aerodynamic design of a CRT with low pressure stage stator is performed and the numerical tools are employed to study its flow field and aerodynamic performance. The results show that concave shroud can reduce the reaction in the top and the oppocite C-shape work distribution can increase the difference in the angle radial distribution at the low pressure stage stator outlet.
2. The effects of the bowed stator blade on the aerodynamic performance of VCRT are studied. The variations in the flow field and the efficientcy change in the high/low pressure stages due to the different stator bowed angles are showed. The investigations of the influence mechanism of bowed blade on the VCRT aerodynamic performance are carried out. The results indicate that stator with small bowed angle is benifical to the VCRT efficiency.
3. Steady/unsteady numerical simulations are performed to reveal the hot streak effections on the radial secondary flow and on the vortex in the VCRT rotor passages. The results show that hot streak can reinforce the radial secondary flow and strength the root passage vortex and wake vortex at high pressure stage rotor passages. The results also show that hot streak can weaken the tip leakage vortex at the high pressure stage rotor passages and weaken the the root passage vortex at low pressure stage rotor passages.
4. The influences of hot streak on the blade surface heat load, the blade tip heat load and the endwall heat load are studied. The study indicates that the heat load is affected by the hot streak, radial secdory flows, leakage vortex and so on. The results show that the heat loat on the aft part of high pressure rotor tip and the heat loat on the aft part of low pressure rotor tip are heavier in hot streak condition due to the passing hot gas. The results also show that the heat load on the aft part of high pressure rotor hub and the heat load on the low pressure stage rotor hub are heavier in the hot streak condition due to the radial secdory flows of hot gas. In addition, the hot gas addrvied to the blade tip remove from shroud due to the leakage vortex, so the heat load on the shroud is lighter in hot streak condition.
5. The investigation of hot streak effects on the aerodynamic performance of VCRT is performed. The results indicate that the work of hot gas at the midspan increases and the work of cool gas at the endwall decrease in hot streak condition. The results also show that the efficiency at midspan decrease due to the losing energy of hot gas and the the efficiency at endwall increase due to the getting energy of cool gas in hot streak condition.
1.对某1+1对转涡轮进行了气动设计,并通过数值模拟的手段对其流场和气动性能进行了分析,总结出了相关设计特征。研究发现涡轮上端壁采用下凹型的曲线有利于降低叶顶反动度,低压级采用“反C”型出功分配将导致低压导叶出口气流角的径向差异较大。
2.研究了导叶弯曲对1+1/2对转涡轮气动性能的影响,重点研究了导叶在不同正弯角度和不同反弯角度下导叶通道内流场的变化,气流出口特性的变化以及高低压级涡轮等熵效率的变化,进而得到了导叶弯曲对1+1/2对转涡轮气动性能的影响方式及机理,并发现了导叶在小角度反弯时有利于1+1/2对转涡轮效率的提高。
3.通过对1+1/2对转涡轮在均匀温度进口工况和热斑工况下的定常/非定常数值模拟结果的比较,研究了进口热斑对1+1/2对转涡轮高低压两级转子通道内径向二次流以及涡强度的影响,发现了热斑的引入加剧了气流在高压转子通道内的径向二次流动,增强了高压转子根部通道涡和尾迹涡的强度,但降低了高压转子顶部泄漏涡的强度。还发现了在热斑的影响下,低压转子根部通道涡有所减弱。
4.开展了热斑对1+1/2对转涡轮叶表、叶顶以及端壁热负荷的影响研究,揭示了进口热斑与径向二次流以及顶部泄漏涡等相互作用对1+1/2对转涡轮热负荷的影响机理,发现了在热斑工况下高压转子叶顶尾部和低压转子叶顶尾部的热负荷因高温气体的掠过而增强,高压转子轮毂后端的热负荷和低压转子轮毂的热负荷因高温气体的径向迁移而增强,此外还发现了迁移至叶顶的高温流体在叶顶泄漏涡的卷吸下远离机匣,从而使得机匣的热负荷在热斑工况下有所下降。
5.研究了热斑的存在对1+1/2对转涡轮比功和等熵效率等气动性能的影响,发现了热斑工况下叶中高温流体出功增加,而两端低温流体出功降低；由于叶中高温流体在出功的同时还要向两端低温流体输送能量,因此叶中区域的等熵效率因热斑的引入而降低,两端区域的等熵效率因热斑的引入而升高。
Counter-Rotating turbine (CRT) can offer some significant benefits compared with conventional two-stage turbines, such as the elevated efficiency, the reduced weight, the improved performance of aircraft and so on. So, the aviation powers in Europe and America pay great attentions on the study of CRT, and the CRT has been succsfully applied in the military aero-engines and in the civil aero-engines in those countries. However, the recearch level of the CRT in China is very low, especially in the aerodynamic design and optimization. In addition, researchers have found that hot streak can affect the flow field and heat load in conventional turbines, but the study of the hot steak effects on the flow field, aerodynamic performance and heat load in the Vanless Counter-Rotating Turbine (VCRT) is very few. In view of this background, the investigations on the aerodynamic optimization design and hot steak effects in CRT are showed in this paper. The main content in this paper is listed as follows:
1. An aerodynamic design of a CRT with low pressure stage stator is performed and the numerical tools are employed to study its flow field and aerodynamic performance. The results show that concave shroud can reduce the reaction in the top and the oppocite C-shape work distribution can increase the difference in the angle radial distribution at the low pressure stage stator outlet.
2. The effects of the bowed stator blade on the aerodynamic performance of VCRT are studied. The variations in the flow field and the efficientcy change in the high/low pressure stages due to the different stator bowed angles are showed. The investigations of the influence mechanism of bowed blade on the VCRT aerodynamic performance are carried out. The results indicate that stator with small bowed angle is benifical to the VCRT efficiency.
3. Steady/unsteady numerical simulations are performed to reveal the hot streak effections on the radial secondary flow and on the vortex in the VCRT rotor passages. The results show that hot streak can reinforce the radial secondary flow and strength the root passage vortex and wake vortex at high pressure stage rotor passages. The results also show that hot streak can weaken the tip leakage vortex at the high pressure stage rotor passages and weaken the the root passage vortex at low pressure stage rotor passages.
4. The influences of hot streak on the blade surface heat load, the blade tip heat load and the endwall heat load are studied. The study indicates that the heat load is affected by the hot streak, radial secdory flows, leakage vortex and so on. The results show that the heat loat on the aft part of high pressure rotor tip and the heat loat on the aft part of low pressure rotor tip are heavier in hot streak condition due to the passing hot gas. The results also show that the heat load on the aft part of high pressure rotor hub and the heat load on the low pressure stage rotor hub are heavier in the hot streak condition due to the radial secdory flows of hot gas. In addition, the hot gas addrvied to the blade tip remove from shroud due to the leakage vortex, so the heat load on the shroud is lighter in hot streak condition.
5. The investigation of hot streak effects on the aerodynamic performance of VCRT is performed. The results indicate that the work of hot gas at the midspan increases and the work of cool gas at the endwall decrease in hot streak condition. The results also show that the efficiency at midspan decrease due to the losing energy of hot gas and the the efficiency at endwall increase due to the getting energy of cool gas in hot streak condition.
引文
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