Dynamic Stall Characteristics of the Bionic Airfoil with Different Waviness Ratios

A dynamic stall will cause dramatic changes in the aerodynamic performance of the blade, resulting in a sharp increase in the blade vibration load. The bionic leading-edge airfoil with different waviness ratios, inspired by the humpback whales flipper, is adopted to solve this problem. In this study, based on the NACA0015 airfoil, the three-dimensional unsteady numerical simulation and sliding mesh technique are used to reveal the flow control mechanism on the dynamic stall of the bionic wavy leading edge. The effects of the waviness ratio on the dynamic stall characteristics of the airfoil are also investigated. The results show that the peak drag coefficient is dramatically reduced when a sinusoidal leading edge is applied to the airfoil. Although the peak lift coefficient is also reduced, the reduction is much smaller. When the waviness ratio R is 0.8, the peak drag coefficient of the airfoil is reduced by 17.14% and the peak lift coefficient of the airfoil is reduced by 9.20%. The dynamic hysteresis effect is improved gradually with an increasing waviness ratio. For the bionic airfoil with R = 1.0, the area of the hysteresis loop is the smallest.

Numerical Simulation Research on Radial Force of Centrifugal Pump with Guide Vanes

To reveal the internal unsteady flow state of the guide vane centrifugal pump, in this paper, the standard SST k‐ω turbulent flow model is used for unsteady numerical simulation of the centrifugal pump. The characteristics of the flow field inside the centrifugal pump are analyzed, the resultant force and vector distribution of the radial force of the guide vane and impeller of the centrifugal pump under different flow rates are obtained, which were verified by experiments. The results show that the main reason of radial force of the impeller is the pressure asymmetry in each flow passage. The radial force will show periodic fluctuations due to the rotor-stator interference between the impeller and the guide vanes under different flow rates. The radial force on the impeller decreases gradually with the increase of the flow, the distribution is hexagonal or hexagonal shape, and the number of impeller blades is the same. The results can provide reference for the design of impeller and guide vane of centrifugal pump.

Effects of Rim Seal Geometries on Aerodynamic Performance and Rotor Platform Cooling in a One-Stage Turbine

Rim seals are used to prevent ingestion of hot gas into turbine rim cavities. As these cavities are not actively cooled, high-pressure air, known as purge flow, is taken from the compressor and introduced beneath the platform to prevent hot gas from penetrating through the gaps between stationary and rotating parts. Meanwhile, the purge flow impacts the aerodynamic performance and provides secondary-order cooling on the rotor platform. In this paper, the effect of four kinds of engine realistic rim seals on flow fields and rotor platform cooling is investigated with constant coolant rate of 1.0% in a one-stage highly-loaded turbine using an unsteady numerical simulation. The numerical simulation is validated by extensive aerodynamic and heat transfer experimental data. Flow fields and film cooling on the rotor platform and turbine overall aerodynamic performance are discussed and compared in detail for four different rim seal geometries at a design condition of mainstream flow. Case 1 is the conventional radial rim seal geometry and is taken as the baseline (radial injection) rim seal geometry for comparisons. Case 2 (with additional cavity) and Case 3 (incline injection) are obtained by modifying the rim seal geometries based on Case 1. In particular, Case 4 (end wall flank flow), a new structure, is proposed to improve film cooling effectiveness on the rotor hub platform. Comparisons among four rim seal geometries show that the new rim seal structure significantly alters the flow structures near the rotor platform by modifying the development and migration of the purge flow and ingestion of hot gas. The highlight is that the new rim seal geometry of Case 4 could double the film cooling effectiveness or even higher, while at the same amount of coolant. Meanwhile, the aerodynamic performance does not decrease obviously than the other rim seal structures.

Effect of Blade Outlet Angle on Radial Force of Marine Magnetic Drive Pump

To research the effects of the blade outlet angle on the performance and the radial force of the marine pump, the unsteady numerical simulation of the four different models is carried out. The radial forces on the impeller and the blades are obtained under different flow rate conditions. The time and frequency domain characteristics of radial resultant force on the impeller and the blades are analyzed and those of the impeller torque are researched. The results show that the radial forces of the impeller and the blades increase with the increase of the blade outlet angle at the same flow rate. With the same blade outlet angle, the radial forces decrease with the increase of the flow rate. The roundness of radial force vector diagram becomes more obvious with the decrease of the blade outlet angle. The root mean square (RMS) of radial force on the blades is about 30% of that on the impeller. The main frequency of radial force on the impeller and the blades is the axial passing frequency (APF), and that of impeller torque is the blade passing frequency (BPF), and there are peaks at the blade frequency multiplier. At the same flow rate, the main frequency and maximum fluctuation amplitudes on the impeller and the blades increase with the increase of the blade outlet angle. Meanwhile, the impeller torque increases with the increase of the blade outlet angle. With the same blade outlet angle, the main frequency, maximum fluctuation amplitudes, and the impeller torque decrease with the increase of the flow rate. The amplitude difference decreases with the increase of the flow rate. The blade outlet angle has an obvious greater influence on the radial forces and fluctuation at the small flow rate. The vibration test shows that the vibration intensities of model 25 and model 35 are less than 2.5 mm/s, and the vibration intensity of model 25 is about 0.2 mm/s less than that of model 35.

An Unsteady Momentum Source Method and Its Application in Simulation of Hovering Rotor

The efficiency and accuracy of numerical simulation on power unit is the key to study the relevant aerodynamic layout with multiple rotating power units. However, the numerical simulation of the power unit using real geometry all faces the problem of low solution efficiency. Taking the rotor hovering state as an example, the real blade was firstly simplified and replaced by a thin mesh disk to establish the effective momentum source method. Then, using fan-shaped mesh region that changes with time to replace real blade and simulate the rotation, the unsteady momentum source method which could get the revolution of tip vortex was proposed. The results show that the momentum source method with the input of accurate blade force distribution can simulate rotor wake better, and the influence that blade geometry acts on wake mainly reflects in the blade force distribution. In addition, the unsteady momentum source method can simulate the revolution of tip vortex, and its consumptions of computing resources and calculation time are only about 1/8 of the unsteady numerical simulation based on the real geometry.

Investigation on the unsteady pressure fluctuation characteristic in the blade tip seal of steam turbine based on spectrum

The paper presents the unsteady numerical simulation results of tip leakage flow in high pressure steam turbines, and also presents the influence analysis of leakage vortexes on pressure fluctuation characteristics of rotor cascade under different blade tip seal clearances. The numerical method for calculating is based on the large eddy simulation turbulence model and the pressure fluctuation of rotor cascade which induced by the unstable leakage vortexes is obtained by frequency spectrum analysis. The results show that the vortex frequencies in tip seal cavity contain both the wheel rotating frequency and the high frequency caused by the tip leakage flow breaking into small scale vortexes. The unsteady characteristics of tip leakage flow also induce steam exciting force which changes with the time.