摘要：本文从微观的角度，分析了排海工程扩散管内海水入侵与冲洗的临界水力特点，并通过理论分析和物理模型试验的相互验证，得出了上述临界水力条件的判别关系式，提出了判别方法，并由此得到了深圳妈湾排海工程防止海水入侵的临界排放流量和出现海水入侵后的最小冲洗流量，为排海工程在非设计条件下的运行管理提供了依据。

摘要：本文在物理模型试型的基础上，通过理论分析和试验结果的相互验证，认为“悬浮指标”和“水流挟沙力”可作为泥沙沉积之水力条件的有效判据，且提供了判断方法，并由此得出了深圳妈湾排海工程防止泥沙沉积的临界排放流量，最后提出了防止泥沙沉积的运行管理防范措施和建议。

摘要：The governing equations are derived by circumferentially averaging the three-dimensional(3D) Navier-Stokes equations,which are solved using a time marching finite volume *** Euler throughflow model and Navier-Stokes(N-S) throughflow model are employed to investigate the performance and flow fields of a highly loaded transonic single-stage fan ATS-2 and a four-stage *** results are compared with the experimental and three-dimensional computational *** shows that the throughflow models can provide reasonable performance characteristics and N-S throughflow model gives better predictions in endwall regions.A throughflow computation n in which all the non-axisymmetric terms are included has been performed at off-design condition and the radial distributions of the flow field can be well described.

摘要：The shear-stress transport(SST)turbulence model is incorporated into Navier-Stokes equations to simulate a turbomachinery flowfield.A staggered finite volume method is used to make the mean flow equations and turbulence model equations strongly coupled and enhance the stability of the numerical *** implicit treatment of the source terms is applied to the SST model.A steady state solution is obtained using five-stage Runge-Kutta time-stepping scheme with local time stepping and residual smoothing to accelerate convergence. The wall distance d,a key parameter in the SST model,is solved by a partial differential *** validations of the code are conducted on rotor 37,wp11 at design and off-design conditions by comparison with measurements and the Spalart-Allmaras(SA)turbulence *** flow within the tip is calculated with a multi-block grid.

摘要：This paper presents the investigation of the effects of suction side squealer tip on the performance of an axial *** experiment is carried out in a single-stage large-scale low-speed *** investigated tip geometries include flat tip as the baseline and suction side squealer *** tip clearance of the baseline is 0.5% of the blade *** static pressure rise characteristic curves of both the rotor and the stage are *** flow field at the exit of the rotor is measured by a 5-hole probe under design and off-design *** static pressure on the endwall of the rotor passage is also *** results show that the pressure rise characteristic curves obtained by measuring the pressure on the end wall are almost unchanged by using the suction side squealer *** measuring results of the 5-hole probe show the static pressure and the total pressure in tip region is slightly greater than that of the flat tip at the design condition at the exit of the *** also leads to greater av-eraged static pressure rise and total *** the near stall condition,the averaged static pressure and total pressure is lower than the baseline which is related to the redistribution of the blade load caused by the suction side squealer tip.

摘要：An experimental study is conducted to investigate the influences of blade tip winglet on the flow field of a compressor cascade. The tests are performed in a low speed linear cascade with stationary endwall, with three blade tip configurations, including the baseline tip, the suction-side winglet tip and the pressure-side winglet tip. The flowfield downstream of the cascade is measured using five-hole probe, from which the three-dimensional velocity field, vorticity field and pressure field are obtained. Static pressure measurements are made on the endwall above the blade row using pressure taps embedded in the plywood endwall. All measurements are made at both design and off-design conditions for tip clearance level of about 2 percent of the blade chord. The results revealed the incidence variation significantly affects the secondary flow and the associated loss field downstream of the cascade, where the tip leakage vortex and passage vortex exist as the major contributors on the field. The winglet geometry arrangements can change the trajectory of the tip leakage vortex. The suction-side winglet tip blade provides a lower overall total pressure loss coefficient when compared to the baseline tip blade and pressure-side winglet tip blade at all incidence angles.

摘要：Increasing demand for downsizing of engines to improve CO2 emissions has resulted in renewed efforts to improve the efficiency and expend the stable operating range of the centrifugal compressors used in petro-chemical equipment and turbochargers. The losses in these compressors are dominated by tip clearance flow. In this paper, the tip clearance flow in the subsonic impeller is numerically investigated. The nature of the tip clearance in inducer, axial to radial bend and exducer are studied in detail at design and off-design conditions by examining the detailed flow field through the clearance and the interaction of the clearance flow with the shear effect with the endwalls. The correlation between blade loading and span wise geometry and clearance flow at different locations are presented.

摘要：The valuation of the hydraulic performance of a centrifugal pump with pre-whirl regulation of the inlet guide vanes was studied experimentally by varying the pre-whirl angle from -60° to 60° with distances between the inlet guide vanes and the impeller inlet of 280 mm, 380 mm and 460 mm. The efficiency-flow curves and the characteristic curves were obtained for the pump for various operation conditions. The experiment results demonstrated that the pre-whirl regulation widened the high efficiency zone and improved the hydraulic performance for off-design conditions with the proper pre-whirl angle. The axial distance between the inlet guide vanes and the impeller inlet influenced the pre-whirl regulation effect of the inlet guide vanes with the best pre-whirl regulation effect obtained for an axial distance of 380 mm. These results showed that an appropriate axial distance between the inlet guide vanes and the impeller inlet can improve the fluid flow at the impeller entrance with pre-whirl regulation for centrifugal pumps.