共查询到20条相似文献,搜索用时 78 毫秒
1.
汽轮机次、末两级弯扭静叶的工程设计与实验研究 总被引:2,自引:0,他引:2
本文的主要目的是讨论弯扭叶片在大功率汽轮机低压缸末级和次东级的工程应用问题。具有弯扭叶片的通流设计方法采用基于求解欧拉方程的S2流面正问题计算,静叶栅的实验是在环形叶栅实验风洞上进行的,通过对计算结果和实验结果的分析,本文讨论了弯扭叶片在次、末两级中对改善流场的作用。 相似文献
2.
3.
4.
5.
6.
7.
1实验装置与模型叶片倾斜和弯曲的概念是针对小径高比环形叶栅提出来的。在短叶片环形叶栅中采用弯曲叶片的效果如何,本文作者对此进行了研究。同时也讨论了边界条件对静叶出口流场的影响。本实验是在哈尔滨工业大学的环形叶栅风洞上进行的。实验用的三套叶栅为:(1)常规径向叶片;(2)两端倾斜角为15”的弯曲叶片;(3)两端倾斜角为22“的弯曲叶片。其特性参数为:径高比为10.553,弦长b—31.Zmm,叶型安装角风一45.3“,进气角。0—90”,几何平均出气角。1—15”。出口马赫数M=0.26左右。(1)()(3)均为等截面叶栅,(2)… 相似文献
8.
9.
10.
11.
The results of the experimental study into the damping of flexural vibrations in turbofan blades with trailing edges tapered according to a power-law profile are reported. Trailing edges of power-law profile (wedges), with small pieces of attached absorbing layers, materialise one-dimensional acoustic black holes for flexural waves that can absorb a large proportion of the incident flexural wave energy. The experiments were carried out on four model blades made of aluminium. Two of them were twisted, so that a more realistic fan blade could be considered. All model blades, the ones with tapered trailing edges and the ones of traditional form, were excited by an electromagnetic shaker, and the corresponding frequency response functions have been measured. The results show that the resonant peaks are reduced substantially once a power-law tapering is introduced to the blade. An initial study into the aerodynamic implications of this method has been carried out as well, using measurements in a closed circuit wind tunnel. In particular, the effects of the trailing edge of power-law profile on the airflow-excited vibrations of the fan blades have been investigated. It has been demonstrated that trailing edges of power-law profile with appropriate damping layers are efficient in reduction of the airflow-excited vibrations of the fan blades. The obtained results demonstrate that power-law tapering of trailing edges of turbofan blades can be a viable method of reduction of blade vibrations. 相似文献
12.
13.
The coupled vibration modes of a rotating blade-disc system are calculated by a finite element method. It is assumed that a large number of identical blades are present, such that the resulting blade loadings on the disc can be considered continuously distributed around the rim of the disc. The disc may have arbitrary profile, and the blades may be tapered and twisted, thus closely representing practical axial flow turbomachine configurations. The effects of rotation, thermal stress, and transverse shear and rotatory inertia in discs of moderately thick profile are readily incorporated into the finite element model. Calculated values of frequencies are compared with experimental data obtained on non-rotating models, and the convergence of the solution is examined by comparison with exact solutions, which can be obtained for configurations of simple geometry. Excellent agreement with experimental data is obtained when using remarkably few elements in the mathematical model, and convergence of the solution is extremely rapid. 相似文献
14.
The endwall effect has a great impact on the aerodynamic performance of compressor blades. Based on three conventional near-endwall blade modeling methods of bowed blade, endbend blade and leading-edge strake blade (LESB), two combined optimization design methods of highly loaded blades have been developed considering the endwall effect in the current study, i.e., the bowed blade combined with the LESB (bowed LESB blade) and the endbend blade combined with the LESB (endbend LESB blade). Optimization designs were conducted for a compressor cascade with low solidity by using the two combined modeling methods and the three conventional modeling methods, and the optimization results were compared and analyzed in detail. The results showed that the five optimization modelling methods could all improve the performance for the original cascade, and the optimized cascade with the bowed LESB modeling method has the best aerodynamic performance. The total pressure loss of the optimal bowed LESB cascade was only 40.3% of that in the original cascade while reducing the solidity of the original cascade from 1.53 to 1.25 and keeping the static pressure rise and diffusion factor at the same level as the original one. Among the optimal cascades, the radial migration height of the low-energy fluid and the corresponding vortex have great effects on the aerodynamic performance, and the optimal bowed LESB cascade is superior to the other optimal cascades in this aspect. 相似文献
15.
叶片弦向倾斜对损失发展的影响及叶片反弯降低损失机理的研究 总被引:2,自引:1,他引:1
早在六十年代初期,Smith提出了弦向倾斜叶片 ̄[1]。叶片的这种倾斜集叶片的后掠(叶片展向与气流不垂直)和上反(叶片表面与端壁斜交)于一身。根据理论分析可知,弦向倾斜叶片与周向倾斜叶片比较,在相同倾斜角下,它更能有效地抑制通道涡的形成和发展 ̄[2]。但是,到现在为止还没有实验数据证实这一计算结果。本文继文献 ̄[3]详细测量了弦向倾斜叶片叶栅由栅前至栅后诸截面上的气动参数。实验结果表明,弦向倾斜对损失的发展起到了与周向倾斜相类似的作用,但是前者比后者减小了叶栅进口段的流向逆压梯度,从而降低了二次旋涡损失。本文还测量了大转角常规直叶栅与反弯叶片叶栅端壁与叶片表面上的静压分布,探讨了反弯叶片降低损失的原因,认为:减小叶栅进口段流向逆压梯度,在叶片吸力面前部形成垂直于端壁的平行静压等值线、在中部形成反“C”型静压等值线,以及在流道内建立沿叶高的反“C”型静压分布,是反弯叶片降低损失的三要素。 相似文献
16.
现有方法常将相机从下至上拍摄标记物图像,当桨叶扭转幅度较大时,相机主光轴与标记物平面法向量存在明显夹角,导致拍摄图像存在透视畸变现象,从而引发较大测量误差。为解决上述问题,提出一种基于透视变换的直升机桨根扭转角测量方法。首先,将靶标垂直固定在桨叶下方,相机正对桨毂拍摄图像。其次,计算桨叶在低速拉平状态下待测方位与正方位靶标图像中的四个顶点坐标,并求解待测方位的透视变换矩阵,然后利用透视变换矩阵对桨叶高速运动状态下待测方位拍摄的畸变图像进行校正。最后,求得基准图像与校正后图像中的圆心坐标,进而计算出待测方位扭转角。实验结果表明,各方位测量误差均小于0.2°。该方法不但测量精度高,而且具有多方位动态测量的优点,在直升机旋翼桨叶运动参数测量领域具有良好的应用前景。 相似文献
17.
Bo-Wun Huang 《Journal of sound and vibration》2006,294(3):486-502
The effect of a near root local blade crack on the stability of a grouped blade disk is investigated in this paper. A bladed disk comprised of periodically shrouded blades is used to simulate the coupled periodic structure. The blade crack is modeled using the local flexibility with coupling terms. The mode localization phenomenon introduced by the blade crack on the longitudinal and bending vibrations in the rotating blades has also been considered. Using the Galerkin's method, the imperturbation equations of a bladed disk in which one of the blades is cracked, subject to fluctuations in the rotation speed, can be derived. Employing the multiple scales method, the boundaries of the instability zones in the mistuned turbo blade system are approximated. Numerical results indicate that an additional unstable zone is introduced near the localization frequency and the regions of unstable zones are varied with the crack size and fluctuations in disk speed. 相似文献
18.
19.
Scale effects and dynamic similarity in the bending vibrations of helicopter rotor blades are examined by expressing the first three modes of bending vibration of a uniform, conventional rotor blade by a series of Legendre polynomials as suggested by Wilde and others. The natural frequency ratios for these three modes are then determined as functions of a dynamic similarity parameter over the entire range of designs and operating conditions from very flexible, rapidly rotating blades to highly rigid, slowly turning conditions. 相似文献
20.
诱导轮泵的汽蚀特性和内部流场的研究 总被引:5,自引:1,他引:4
对二个叶片的平板螺旋形诱导轮泵的汽蚀性能,叶轮内的空泡发展和内部流动进行了测试。发现随着吸入压力的降低,二个叶片上原来同样发展的空泡之间有时会失去平衡,出现一个叶片的空泡激剧缩小,而另一个叶片的空泡随之增大这种交错叶片空泡的现象。这种现象有时会使诱导轮的理论扬程和实际扬程急速下降。利用上述测试结果对该现象引起杨程下降的机理作了探讨。 相似文献