共查询到20条相似文献,搜索用时 953 毫秒
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增加燃气初温是提高燃气轮机效率的主要途径。为了确保充分冷却透平叶片与轮盘,在防止燃气入侵盘腔的同时降低冷气量,需要针对盘腔系统内的流动特性展开研究。高压涡轮盘腔系统含有预旋腔等多个腔室,通过转静封严或旋转孔相互连通。尽管国内外学者针对盘腔系统开展了一系列研究,但大部分以单一腔室为研究对象,很少考虑多个腔室,尤其是预旋腔上下游盘腔对预旋腔内流动特性的影响。因此,本文以某船用燃机高压涡轮盘腔系统为研究对象,采用CFD方法,模拟了盘腔系统内部的流量分配,预测了斜接受孔和平衡孔的通流能力,分析了盘腔内的压力、温度、速度场分布和涡系结构,并分析了燃气入侵现象。本文的研究结果可为研究复杂盘腔系统提供参考。 相似文献
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针对圆柱腔低频声场的球谐函数分解,提出了基于移动式球形传声器阵列(简称球阵)测量的空间域直接求解法。利用空间域测量数据,在压缩感知(Compressive Sensing,CS)理论框架下通过一次线性方程组求解,获得整体坐标系下的声场展开系数。首先讨论了感知矩阵的列相关性,比较不同球阵形式及球面采样点数目,不同球谐函数截断阶数以及空间测量位置等的影响。随后在飞机舱室模型内利用文中提出的方法求解声场展开系数,再现腔内水平面的声压分布,并与传统球坐标变换方法做比较。实验结果表明,利用空间域直接求解法,通过球面随机挑选10个采样点的刚性球阵在声腔3个位置进行声场测量,不仅能够有效求解声场展开系数,而且声场再现精度更高,同时计算效率也显著提高。 相似文献
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旋转盘腔流场速度与压力的实验研究 总被引:5,自引:1,他引:4
本文描述一个旋转盘腔流场的实验研究。该盘腔由一个旋转盘,一个静止盘及静止的外围屏组成.实验表明在盘腔的两个盘面上都有边界层形成,在边界层中,流体除有切向速度外,还有沿径向的二次流存在。在边界层外的核心区中径向速度为零。一般来说,静盘边界层比转盘边界层向紊流转捩地要早。另外,压力的测量表明,在半径较大的区域中压力分布可由“流体以恒角速度旋转”的假设所得的结果近似。 相似文献
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轮背空腔-密封气对CAES向心涡轮变工况流动损失的影响 总被引:1,自引:0,他引:1
本文以国内首套MW级压缩空气储能(CAES)系统末级向心涡轮为研究对象,通过数值模拟分析了变工况条件下轮背空腔-密封气对等熵效率和流场结构的影响.结果表明:在求解中考虑轮背空腔-密封气结构能够使等熵效率数值解的偏差减小0.7%;随涡轮进口压力增加,轮背空腔泄漏流由叶片吸力面中部叶高区域逐渐向轮毂转移,流动损失先增加后减小;合理降低轮背空腔泄漏气体的轴向速度,能够减弱轮背空腔-密封气结构对等熵效率的负面影响,使向心涡轮在较宽的变工况范围内都保持高效运行. 相似文献
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感应加速腔有径向馈入和轴向馈入两种常用的脉冲功率馈入方式。在理论上分析了不同功率馈入方式对感应加速腔输出电压平顶的影响,并对分析结果进行实验论证。实验采用1B2C结构,用相同的脉冲功率源馈入径向腔和轴向腔,测量此两种加速腔的电压波形。测得轴向腔±1%电压平顶时间为61 ns,径向腔±1%电压平顶时间为62 ns,两种腔都可满足±1%电压平顶大于60 ns的要求。此外对不同功率馈入方式导致的横向阻抗的变化进行了数值模拟,分别计算了采用这两种馈入方式的加速腔模型的横向阻抗,发现轴向加速腔的横向阻抗较小。 相似文献
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两回转体并联入水过程中,双空泡在空间上相互干扰,使得单个入水空泡呈现非对称特性.本文基于势流理论,在现有二维轴对称入水空泡计算模型的基础上,对空泡干涉区域的三维流动进行简化,将相对流动对空泡发展的约束简化为约束势,分析了两回转体轴线内外两侧的空泡形态变化;基于非线性假设,引入影响函数,给出了空泡在三维空间演化的计算模型,并分析了同步并联入水过程空泡的三维演化特性.结果表明:回转体入水过程流场速度势可以看作由一个随回转体运动的点源和位于空泡轴线处的线源叠加产生;在并联入水过程中,双空泡演化在空间呈镜面对称,空泡间的相互扰动可以通过引入有势壁面进行分析;并联入水空泡半径随极角的变化与空泡截面所处深度有关,在靠近闭合点附近的抑制演化区空泡截面半径随极角的增大而逐渐减小,远离闭合点处的抑制演化区空泡截面半径随极角的增大而增大,空泡加权半径规律相反. 相似文献
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The inflow ahead of a rotating propeller attached to a container ship model was visualized using a two-frame particle image
velocimetry (PIV) technique. For illuminating the inflow region, a transparent window was installed at the stern of the ship
model. Ensemble-averaged mean velocity fields were measured at four different blade phases under the design loading condition.
The characteristics of the inflow in the upper plane above the propeller axis are quite different from those below the propeller
axis. In the far upstream region above the propeller axis, most of the inflow comes from the hull wake and the axial velocity
is very small. As the inflow moves toward the propeller plane, its axial velocity component increases rapidly. In addition,
the variation of the inflow characteristics with respect to phase angle becomes apparent. The thick hull boundary layer and
out-of-plane motion resulting from the propeller rotation produce a large turbulent kinetic energy around the tip of the propeller
blade in the upper inflow region. The axial velocity distribution of the propeller inflow is asymmetric with respect to the
vertical center axis, exhibiting different axial velocities on the port and starboard sides. 相似文献
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In-duct devices are commonly installed in flow ducts for various flow management purposes. The structural construction of these devices indispensably creates disruption to smooth flow through duct passages so they exist as structural discontinuities in duct flow. The presence of these discontinuities provides additional possibility of noise generation. In real practice, in-duct devices do not exist alone in any duct system. Even though each in-duct device would generate its own noise, it might be possible that these devices could be properly arranged so as to strengthen the interference between individual noise; thus giving rise to an overall reduction of noise radiation in the in-duct far field. This concept of passive noise control is investigated by considering different configurations of two structural discontinuities of simple form (i.e., a cavity) in tandem in an unconfined flow and in opposing setting within a flow duct. It is known that noise generated by a cavity in unconfined domain (unconfined cavity) is strongly dependent on flow-resonant behavior within the cavity so the interference it produces is merely aeroacoustic. The objective of the present study is to verify the concept of passive noise reduction through enhancement of aeroacoustic interference due to two cavities by considering laminar flow only. A two-dimensional approach is adopted for the direct aeroacoustic calculations using a direct numerical simulation (DNS) technique. The position and geometries of the cavities and the Mach number are varied; the resultant aeroacoustic behavior and acoustic power are calculated. The numerical results are compared with a single cavity case to highlight the effect of introducing additional cavities to the aeroacoustic problem. Resonant flow oscillations occur when two unconfined cavities are very close and the associated acoustic field is very intense with no noise reduction possible. However, for duct aeroacoustics, it is found that a 7.9 db reduction of acoustic power in the downstream side of the duct or a total reduction of ∼6 db is possible with opposing cavities having an offset of half a cavity length. In addition, the reduction is shown to be free from lock-on with trapped modes of the ducts with cavities. 相似文献
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The results are presented of an investigation of flow-excited acoustic resonance in covered cavities. It is shown that energy is drawn from the mean flow entering a cavity and fed into the acoustic wavefield as a result of impingement of the inflowing jet against a solid boundary. Whether the oscillating wavefield consists of waves running transverse or longitudinal to the inflowing jet strongly depends upon whether the inflow is wall bounded on one side or free. It is also shown that if the exit duct has the characteristics of a diffuser it, too, can have an active influence on the resonance cycle. The conclusions reached are based upon fluctuating pressure measurements and visualization of the flow in a series of two-dimensional and axisymmetric cavity configurations. 相似文献