基于流动控制的无导叶对转涡轮性能研究
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摘要
对转涡轮技术是燃气涡轮发动机的一项关键技术,它在提高发动机推重比以及飞机性能方面具有较大的发展潜力。在1+1/2对转涡轮中,由于其高压动叶具有缩放型流道,使得1+1/2对转涡轮的流场、流量调节规律与具有渐缩型流道的常规涡轮有所不同。因此,深入研究1+1/2对转涡轮的流动特性,并采取有效的流动控制措施降低高压动叶流道内的激波损失以及控制对转涡轮流量,对增加流动稳定性和提高发动机性能具有重要意义。
本文针对1+1/2对转涡轮的流动特征,分别采用在高压动叶吸力面沿展向加凸台、可调高压导叶和高压动叶叶表喷射冷气的流动控制措施,通过数值模拟和叶栅实验对流动控制措施的有效性及控制机理进行了研究,主要研究内容如下：
1.在1+1/2对转涡轮高压动叶吸力面因内伸波导致的分离区设置凸台,通过调整凸台的轴向位置和高度,改变流道通流形状和面积,从而达到抑制分离的目的。采用数值模拟方法,对不同凸台位置和高度的工况进行对比分析,得到了能够有效抑制分离的凸台最优位置和高度,当凸台位于吸力面84%-86%轴向弦长位置,最大高度为1mm,并且与叶表光滑连接时,其对吸力面分离区的抑制效果最佳。
2.由于1+1/2对转涡轮的喉部位于高压动叶中,且高压动叶出口流动沿展向均超音,涡轮流量不随背压的变化而变化,因此采用可调高压导叶的流动控制措施对其流量进行调节。本文运用数值模拟方法对采用可调高压导叶后的1+1/2对转涡轮性能及流场进行了分析,研究了可调导叶开度和涡轮流量、效率、功量、损失等之间的关系,结果表明,采用可调高压导叶能够有效控制1+1/2对转涡轮流量、保持合理的高低压级出功比和较高的涡轮效率。
3.保护高温部件的冷却气体排入叶栅流道对涡轮叶栅的气动性能会产生影响,本文以1+1/2对转涡轮中具有缩放型流道的高压动叶50%叶高截面叶型构成的叶栅为研究对象,采用数值模拟方法针对六个不同轴向位置处喷射冷气对缩放型流道涡轮叶栅性能的影响进行了详细的研究,着重分析了冷气喷射位置、冷气与主流质量流量比等影响因素,结果表明,在吸力面内伸波反射点附近喷射冷气可以减弱内伸波强度,这主要是由于射流冷气滞止了冷气孔前的气流,造成较大的逆压梯度,孔前压力升高,使得内伸波前后压差减小。证明了内伸波反射点附近射流减小内伸波强度的流动控制方法的有效性。
4.利用跨声速平面叶栅实验台针对非设计工况时缩放型流道涡轮叶栅流动特性和冷气喷射对其性能的影响进行了实验研究,并对缩放型流道涡轮叶栅中波系结构随膨胀比的变化做了纹影实验,对不同攻角、不同膨胀比及不同冷气流量时的叶栅进出口参数、叶表静压、端壁静压等进行了测量,实验结果与数值模拟结果符合较好,并且在内伸波作用位置处,实验与数值模拟均捕捉到了内伸波引起的流场变化。实验测得的叶表静压分布和纹影图均表明缩放型流道涡轮叶栅中波系结构随膨胀比的变化与理论分析和数值模拟中的变化过程一致,这些进一步说明了本课题组发展的具有缩放型流道的1+1/2对转涡轮的设计、分析与实验系统的正确性。
Counter-rotating turbine is one of the key technologies of gas turbine engine and it has great potential in elevating thrust-to-weight ratio of aero-engine and improving performance of aircraft. Because the convergent-divergent passage of high-pressure rotor in1+1/2counter-rotating turbine is different from the conventional turbine with convergent passage, the flowfield and the flow control discipline both are different. Meanwhile, the effective flow control methods may be able to further optimize the turbine performance. So the reasonable flow control methods in1+1/2counter-rotating turbine can reduce the shock wave strength and regulate the flow rate, which is significative to strengthen flow stability and improve the aero-engine performance.
Based on the flow characteristic of1+1/2counter-rotating turbine, the flow control methods of the suction surface bump in high-pressure rotor, the variable high-pressure guide vane and the coolant injection in high-pressure rotor are adopted respectively, and the validity of flow control is verified by numerical simulations and experiments. The main contents in this paper are listed as follows:
1. The bump is fixed on the separation region of high-pressure rotor suction surface, the shape and the area of flow passage has been change with the adjust of the bump position and height. The separation region is suppressed effectively because of the bump. The different conditions of bump position and height are analyzed by numerical simulation and the optimum bump is found finally. When the suction surface bump is fixed in84%～86%axial chord length and the maximum height of the bump is1mm, the bump can inhibit the boundary layer separation effectively.
2. Because the throat of the1+1/2counter-rotating turbine locates in the high-pressure rotor and the flow at the outlet of the high-pressure rotor is supersonic, the flow rate of the1+1/2counter-rotating turbine is uniform with the different outlet pressure. So the variable high-pressure guide vane is applied to adjust the turbine flow rate. A detailed numerical simulation has been carried out to investigate the1+1/2counter-rotating turbine performance and flowfield with different openings of high-pressure guide vane, the relationship between the opening and flow rate, efficiency, power and losses is investigated. The results indicate that the variable high-pressure guide vane can effectively control the flow rate of1+1/2counter-rotating turbine, keep the reasonable specific work ratio of high-pressure turbine to that of low-pressure turbine and achieve the good efficiency.
3. The coolant protected the high temperature units flows into the cascade passage, which brings some influence on the aerodynamic performance, the high-pressure rotor with convergent-divergent flow passage in the1+1/2counter-rotating turbine is the object of study. A detailed numerical simulation has been carried out to study the influence of the coolant injection on the performance of the convergent-divergent turbine cascade. The cooling-hole position and the massflow ratio between coolant and mainstream are the main influence factors. The numerical results show that the coolant injected from the suction surface where the inner-extending shock impinges can change the shock strength. The main reason is that a large adverse pressure gradient caused by the coolant injection results in the rising pressure before cooling holes and the decreasing the difference of pressure on both side of the shock.
4. Some cascade experimental investigations are performed to study the influence of the coolant injection on the cascade performance at off-design conditions in a transonic cascade test facility, meanwhile the schlieren graphs of the shock wave system in the convergent-divergent turbine cascade has been obtained at different expansion pressure ratio. The cascade inlet and outlet parameters, the blade surface static pressure and the endwall static pressure is measured at conditions of different attack angles, different expansion pressure ratios and different coolant flowrate. The results of experiment and numerical simulation are accordant and the flowfield change caused by the inner-extending shock is captured, which indicates that the design, analysis and the experimental system of1+1/2counter-rotating turbine developed by our group is credible.
本文针对1+1/2对转涡轮的流动特征,分别采用在高压动叶吸力面沿展向加凸台、可调高压导叶和高压动叶叶表喷射冷气的流动控制措施,通过数值模拟和叶栅实验对流动控制措施的有效性及控制机理进行了研究,主要研究内容如下：
1.在1+1/2对转涡轮高压动叶吸力面因内伸波导致的分离区设置凸台,通过调整凸台的轴向位置和高度,改变流道通流形状和面积,从而达到抑制分离的目的。采用数值模拟方法,对不同凸台位置和高度的工况进行对比分析,得到了能够有效抑制分离的凸台最优位置和高度,当凸台位于吸力面84%-86%轴向弦长位置,最大高度为1mm,并且与叶表光滑连接时,其对吸力面分离区的抑制效果最佳。
2.由于1+1/2对转涡轮的喉部位于高压动叶中,且高压动叶出口流动沿展向均超音,涡轮流量不随背压的变化而变化,因此采用可调高压导叶的流动控制措施对其流量进行调节。本文运用数值模拟方法对采用可调高压导叶后的1+1/2对转涡轮性能及流场进行了分析,研究了可调导叶开度和涡轮流量、效率、功量、损失等之间的关系,结果表明,采用可调高压导叶能够有效控制1+1/2对转涡轮流量、保持合理的高低压级出功比和较高的涡轮效率。
3.保护高温部件的冷却气体排入叶栅流道对涡轮叶栅的气动性能会产生影响,本文以1+1/2对转涡轮中具有缩放型流道的高压动叶50%叶高截面叶型构成的叶栅为研究对象,采用数值模拟方法针对六个不同轴向位置处喷射冷气对缩放型流道涡轮叶栅性能的影响进行了详细的研究,着重分析了冷气喷射位置、冷气与主流质量流量比等影响因素,结果表明,在吸力面内伸波反射点附近喷射冷气可以减弱内伸波强度,这主要是由于射流冷气滞止了冷气孔前的气流,造成较大的逆压梯度,孔前压力升高,使得内伸波前后压差减小。证明了内伸波反射点附近射流减小内伸波强度的流动控制方法的有效性。
4.利用跨声速平面叶栅实验台针对非设计工况时缩放型流道涡轮叶栅流动特性和冷气喷射对其性能的影响进行了实验研究,并对缩放型流道涡轮叶栅中波系结构随膨胀比的变化做了纹影实验,对不同攻角、不同膨胀比及不同冷气流量时的叶栅进出口参数、叶表静压、端壁静压等进行了测量,实验结果与数值模拟结果符合较好,并且在内伸波作用位置处,实验与数值模拟均捕捉到了内伸波引起的流场变化。实验测得的叶表静压分布和纹影图均表明缩放型流道涡轮叶栅中波系结构随膨胀比的变化与理论分析和数值模拟中的变化过程一致,这些进一步说明了本课题组发展的具有缩放型流道的1+1/2对转涡轮的设计、分析与实验系统的正确性。
Counter-rotating turbine is one of the key technologies of gas turbine engine and it has great potential in elevating thrust-to-weight ratio of aero-engine and improving performance of aircraft. Because the convergent-divergent passage of high-pressure rotor in1+1/2counter-rotating turbine is different from the conventional turbine with convergent passage, the flowfield and the flow control discipline both are different. Meanwhile, the effective flow control methods may be able to further optimize the turbine performance. So the reasonable flow control methods in1+1/2counter-rotating turbine can reduce the shock wave strength and regulate the flow rate, which is significative to strengthen flow stability and improve the aero-engine performance.
Based on the flow characteristic of1+1/2counter-rotating turbine, the flow control methods of the suction surface bump in high-pressure rotor, the variable high-pressure guide vane and the coolant injection in high-pressure rotor are adopted respectively, and the validity of flow control is verified by numerical simulations and experiments. The main contents in this paper are listed as follows:
1. The bump is fixed on the separation region of high-pressure rotor suction surface, the shape and the area of flow passage has been change with the adjust of the bump position and height. The separation region is suppressed effectively because of the bump. The different conditions of bump position and height are analyzed by numerical simulation and the optimum bump is found finally. When the suction surface bump is fixed in84%～86%axial chord length and the maximum height of the bump is1mm, the bump can inhibit the boundary layer separation effectively.
2. Because the throat of the1+1/2counter-rotating turbine locates in the high-pressure rotor and the flow at the outlet of the high-pressure rotor is supersonic, the flow rate of the1+1/2counter-rotating turbine is uniform with the different outlet pressure. So the variable high-pressure guide vane is applied to adjust the turbine flow rate. A detailed numerical simulation has been carried out to investigate the1+1/2counter-rotating turbine performance and flowfield with different openings of high-pressure guide vane, the relationship between the opening and flow rate, efficiency, power and losses is investigated. The results indicate that the variable high-pressure guide vane can effectively control the flow rate of1+1/2counter-rotating turbine, keep the reasonable specific work ratio of high-pressure turbine to that of low-pressure turbine and achieve the good efficiency.
3. The coolant protected the high temperature units flows into the cascade passage, which brings some influence on the aerodynamic performance, the high-pressure rotor with convergent-divergent flow passage in the1+1/2counter-rotating turbine is the object of study. A detailed numerical simulation has been carried out to study the influence of the coolant injection on the performance of the convergent-divergent turbine cascade. The cooling-hole position and the massflow ratio between coolant and mainstream are the main influence factors. The numerical results show that the coolant injected from the suction surface where the inner-extending shock impinges can change the shock strength. The main reason is that a large adverse pressure gradient caused by the coolant injection results in the rising pressure before cooling holes and the decreasing the difference of pressure on both side of the shock.
4. Some cascade experimental investigations are performed to study the influence of the coolant injection on the cascade performance at off-design conditions in a transonic cascade test facility, meanwhile the schlieren graphs of the shock wave system in the convergent-divergent turbine cascade has been obtained at different expansion pressure ratio. The cascade inlet and outlet parameters, the blade surface static pressure and the endwall static pressure is measured at conditions of different attack angles, different expansion pressure ratios and different coolant flowrate. The results of experiment and numerical simulation are accordant and the flowfield change caused by the inner-extending shock is captured, which indicates that the design, analysis and the experimental system of1+1/2counter-rotating turbine developed by our group is credible.
引文
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