涡轮叶片凹槽状叶顶非定常流动传热特性的数值研究

为了研究涡轮叶片凹槽状叶顶的非定常流动传热特性,以GE-E3第一级静叶和动叶为研究对象,采用ANSYS-CFX数值求解三维Reynolds-Averaged Navier-Stokes(RANS)和标准k-ω紊流模型。数值预测的叶顶换热系数分布与实验数据吻合良好,从而验证了数值方法的可靠性。数值计算结果表明:静叶尾迹对动叶顶部的流动和换热特性影响显著。压力面侧前缘区域和吸力面中间位置的流场受动静干涉影响显著。叶顶表面的换热系数脉动主要出现在靠近前缘的凹槽底部表面和再附着线附近及吸力面侧肩壁。靠近动叶尾缘区域的换热系数脉动同时受动静干涉作用和下游流场的影响。定常计算得到的换热系数在前缘冲击区和分离线附近高于非定常时均值,在压力面侧肩壁附近小于非定常时均值。定常计算得到的平均换热系数要高出非定常计算结果3.5%。

跨音轴流压气机自循环喷气扩稳试验研究

轴流风扇／压气机稳定性控制一直叶轮机械领域迫切需要解决的难题，特别是对于内部流动复杂的跨音转子。提出以自循环喷气方式作为控制手段，并在一台单级跨音风扇／压气机上进行试验研究。试验中通过白行设计自循环机构在压气机上进行基于自循环的叶顶喷气研究，并考察不同抽气角度和喷气偏航角对压气机稳定裕度和效率的影响，并通过测量机匣壁面非定常压力信号对跨音压气机自循环喷气机构中前端喷气的扩稳机理进行分析。试验结果表明：自循环喷气能够有效拓宽跨音压气机的流动失稳裕度，并取得了8％～15％的扩稳效果，而且能够略微提高压气机峰值点的效率。另外，通过功率谱密度分析，前端叶顶喷气的扩稳机理仍然是影响叶顶间隙泄漏流的非定常性。

轴流压气机叶顶喷气扩稳机理试验研究

轴流压气机叶顶喷气已经被证实能够有效拓宽压气机的失稳裕度。在一台低速单转子轴流压气机上进行叶顶喷气试验研究,采用喷气动量比作为衡量失速裕度改善的指标,并通过改变叶顶间隙和喷气角度对不同喷气量的扩稳效果进行分析,试验中发现随着叶顶喷气动量比的增加,压气机失速裕度的变化会出现两个拐点,即存在两个喷气动量比分界点,并将喷气动量比分界点前后的三个阶段对应的喷气量分别定义为微喷气,大喷气和超大喷气。通过试验测量压气机进出口气动参数以及壁面动态压力信号对喷气动量比分界点前后叶顶喷气扩稳机理进行详细的分析。试验分析结果表明:微喷气扩稳仅仅是因其能够减弱叶顶间隙泄漏涡和叶顶间隙泄漏流非定常性;大喷气则能够同时减小进口气流攻角,推迟叶片吸力面分离和抑制叶顶间隙泄漏涡,推迟叶顶间隙泄漏流非定常性的产生;超大喷气虽能够推迟叶顶间隙泄漏流非定常性的产生,但喷气的影响区域已严重向叶片通道内部转移,甚至影响了压气机的做功能力。

间隙和转速对轴流压气机非定常叶顶泄漏流周向传播特性影响的实验研究

针对一台低速单转子轴流压气机,对不同间隙和转速下非定常叶顶泄漏流诱导的压力波的周向传播特性进行了实验研究。通过机匣壁面上沿叶片弦向和周向分布的动态压力传感器,测量压气机转子叶顶区域流场的压力信号;借助功率谱密度、滤波、空间傅里叶变换等方法,分析了非定常波动的频率特性、传播速度和周向模态数的变化。结果表明,小间隙时叶顶泄漏流波动强度减弱;转速不变时减小间隙或间隙不变时提高转速,都将使得相同流量系数时叶顶泄漏流的波动频率增大。对各间隙和转速组合,随压气机节流,传播速度增大,周向模态数减少.转速不变时减小间隙,将使得相同流量系数时的传播速度和模态数增大;对同一间隙的相同流量系数,转速改变对模态数和传播速度无明显影响。

轴流压气机叶顶间隙泄漏流的周向传播特性实验研究

在一台单转子低速轴流压气机上,以叶顶间隙泄漏流非定常性为切入点,通过实验测量沿弦向和周向的壁面非定常压力,分析了叶顶端区非定常波动特征沿叶片弦长的调频特性。研究了占主导地位的叶顶间隙泄漏流非定常波动沿周向的传播特征,进一步分析叶顶间隙泄漏流非定常性波动到失速先兆信号产生的演变规律。实验结果表明,由叶顶间隙泄漏流非定常性波动主导的叶顶端区流场在压气机节流过程中,其周向传播速度逐渐增加,直到失速先兆的产生。由此可以判断,叶顶间隙泄漏流非定常性是失速先兆信号分析和预测的流场依据,为澄清和理解叶顶间隙泄漏流非定常和失速先兆至失速的不同流动特征的统一流体力学机理提供指导。

The Self-induced Unsteadiness of Tip Leakage Flow in an Axial Low-Speed Compressor with Single Circumferential Casing Groove

Numerical investigation on the self-induced unsteadiness of tip leakage flow(TLF) for an axial low-speed compressor with smooth wall and six single grooved casings are presented. A ten-passage numerical scheme is used to solve the unsteady Reynolds averaged Navier-Stokes(URANS) equations. It is found that the single grooves at various axial locations could have a large impact on the self-induced unsteadiness and the stall margin improvement(SMI) of compressor. The trend of SMI with groove center location demonstrates that the groove located near the mid of blade tip chord generates the best SMI. The worst groove is located about 20% Cax after the blade leading edge. The root-mean-squre of static pressure(RMSP) contours at 99.5% span and fast Fourier transform for the static pressure traces recorded in the tip clearance region for each casing are analyzed. The results demonstrate that the single groove location not only affects the oscillating strength but also the frequency of the unsteady tip leakage flow. At the near-stall point of smooth casing, the self-induced unsteadiness of TLF is enhanced most by the best grooved casing for SMI. While, the self-induced unsteadiness disappears when the worst groove for SMI is added. The characteristic frequency of TLF is about 0.55 blade passing frequency(BPF) with smooth casing. The frequency components become complicated as the single groove moves from the leading edge to the trailing edge of the blade.

Unsteady flow structures in the tip region for a centrifugal compressor impeller before rotating stall

To get an insight into the occurrence and the mechanism of flow unsteadiness in the tip region of centrifugal compressor impellers, the flow in Krain’s impeller is investigated by using both steady and unsteady RANS solver techniques. It is found that the flow unsteadiness on the pressure side is much stronger than that on the suction side. The periodical frequency of the unsteady flow is around half of the blade passing frequency. The originating mechanism of the flow unsteadiness is illustrated with the time-dependent tip leakage flow and blade loading at the tip region. Due to the blockage caused by the joint effects of broken-downed tip leakage vortex, separated fluids and tip leakage flow at downstream, a low pressure region is formed on the pressure side, consequently the blade loadings is altered. In turn, the changed blade loadings will alter the intensity of tip leakage flow. Such alternative behavior finally results in the periodic process. By comparing the calculated flow field in the cases of single-passage and four-passage models, it is confirmed that the investigated flow unsteadiness is confined in each single passage, as no phase differences are found in the model of four passages. This is different from the situation in axial compressor when the rotating instability is encountered. The flow unsteadiness only occurs at the working conditions with small mass flow rates, and the oscillation intensity will be enhanced with the decrease of mass flow rate. When the mass flow rate is too small, the flow unsteadiness in a single passage may trigger rotating stall, as the disturbance propagates in the circumferential direction.