Two Aspects of Cavitation Damage in the Incubation Zone: Scaling by Energy Considerations and Leading Edge Damage

1980 ◽  
Vol 102 (4) ◽  
pp. 481-485 ◽  
Author(s):  
D. R. Stinebring ◽  
J. William Holl ◽  
Roger E. A. Arndt

This study focused on two aspects of the cavitation damage problem, namely an energy approach to the scaling of cavitation damage in the incubation zone and damage near the leading edge of a test model. The damage to the surface of the models was in the form of small indentations in which no material was removed. For a wide range of velocities namely 14.9 to 59.3 m/s the rate of pit formation per unit area in the maximum damage zone increased by the sixth power of velocity. Furthermore it is shown that the damage rate versus velocity data are in good agreement with three other investigations. The volumes of the pits were found to increase by the fifth power of velocity. A relationship between the volume of a pit and the cavitation bubble collapse energy absorbed was developed. The damage to the leading edge was felt to be due to the reentrant jet striking the leading edge of the cavity creating a short term pressure rise causing the collapse of any cavitation bubbles in this area.

Author(s):  
K. Funazaki

Detailed measurements are performed about time-averaged beat transfer distributions around the leading edge of a blunt body which is affected by incoming periodic wakes from the upstream moving bars. The blunt body is a test model of a front portion of a turbine blade in gas turbines and consists of a semicircular cylindrical leading edge and a flat plate afterbody. A wide range of the steady and unsteady flow conditions are adopted as for the Reynolds number based on the diameter of the leading edge and the bar-passing Strouhal number. The measured heat transfer distributions indicate that the wakes passing over the leading edge cause significant increase in beat transfer before the separation and the higher Strouhal number results in higher heat transfer. From this experiment, a correlation for the heat transfer enhancement around the leading edge due to the periodic wakes is deduced as a function of the Stanton number and it is reviewed by comparison with the other experimental works.


Author(s):  
К.В. Рождественский

В статье приводятся аналитические и численные результаты по динамике и акустике кавитационного пузырька при повышении внешнего давления. В начале рассматривается модельная задача о сжатии пузырька вплоть до коллапса при мгновенном повышении давления. При этом уравнение Рэлея-Плессета рассматривается с учетом газосодержания, поверхностного натяжения и вязкости. Акустическое давление, вызванное сжатием пузырька, записанное в безразмерном виде, определяется как с привлечением формул, так и численным путем. Показано, что если наряду с паром, внутри пузырька имеется некоторое количество газа, скорость его сжатия и акустическое давление оказываются конечными вплоть до полного схлопывания. Кроме того, возможно многократное повторение цикла расширения-сжатия с затуханием амплитуды колебаний. На каждом периоде колебаний вблизи момента времени коллапса (достижения минимального радиуса) наблюдается импульсное возрастание давления. Во второй части аналогичное исследование проводится для случая, когда кавитационный пузырек возникает в закругленной носовой части подводного крылового профиля. При этом демонстрируется зависимость динамического поведения пузырька и вызываемого им в заданной точке контура профиля акустического давления от типа профиля, его толщины и угла атаки. По периоду первого цикла схлопывания спектральные параметры акустического импульса определяются как у эквивалентного треугольного импульса. Presented in this paper are analytical and numerical results on dynamics and acoustics of a cavitation bubble in adverse external pressure gradient. First considered is a model problem of bubble collapse due to instantaneous increase of pressure. Therewith, the Rayleigh-Plesset equation is treated with account of gas content, surface tension and viscosity. Non-dimensional acoustic pressure caused by the compression of the bubble, is determined both with use of relevant formulae and numerically. It is shown that if together with vapor the bubble contains some quantity of gas, than its collapse rate and acoustic pressure during compression turn out to be finite. In addition, multiple expansion compression cycles are possible. For each period of bubble radius variation there occurs near the moment of collapse (moment of reaching a minimum radius) an impulse acoustic pressure rise. In the second part of the paper a similar investigation is carried out for the case when the bubble occurs near the rounded leading edge of a hydrofoil. Demonstrated therewith is the dependence of the bubble dynamic behavior and accompanying acoustic pressure pulses upon the foil type, thickness and angle of attack. Based on the period of the first bubble collapse cycle the spectral parameters of the induced acoustic pressure impulse are determined as for an equivalent triangular impulse.


1996 ◽  
Vol 118 (3) ◽  
pp. 452-460 ◽  
Author(s):  
K. Funazaki

Detailed measurements are performed about time-averaged heat transfer distributions around the leading edge of a blunt body, which is affected by incoming periodic wakes from the upstream moving bars. The blunt body is a test model of a front portion of a turbine blade in gas turbines and consists of a semicircular cylindrical leading edge and a flat plate afterbody. A wide range of the steady and unsteady flow conditions are adopted as for the Reynolds number based on the diameter of the leading edge and the bar-passing Strouhal number. The measured heat transfer distributions indicate that the wakes passing over the leading edge cause a significant increase in heat transfer before the separation and the higher Strouhal number results in higher heat transfer. From this experiment, a correlation for the heat transfer enhancement around the leading edge due to the periodic wakes is deduced as a function of the Stanton number and it is reviewed by comparison with the other experimental works.


1988 ◽  
Vol 110 (2) ◽  
pp. 194-199 ◽  
Author(s):  
A. Shima ◽  
Y. Tomita ◽  
T. Ohno

In relation to the temperature effect in cavitation damage, the collapse of a single bubble in water over a wide range of temperatures was experimentally studied. A spark-induced bubble was observed by using a high speed camera and the impulsive pressure caused by the bubble collapse was measured by means of a pressure transducer. As water temperature increases, the motion of a bubble tends to weaken owing to the increase in saturated vapor pressure of water, and the surface configuration of a bubble becomes highly irregular because of thermal instability. The impulsive pressure depends not only on the bubble size and its distance from a solid wall but also on the water temperature. When the water temperature approaches the boiling point of water, the impulsive pressure abruptly decreases with increasing water temperature. The evidence obtained seems to be associated with the known temperature effect on cavitation damage at high water temperature.


1997 ◽  
Vol 119 (2) ◽  
pp. 292-301 ◽  
Author(s):  
K. Funazaki ◽  
M. Yokota ◽  
S. Yamawaki

Detailed studies are conducted on film effectiveness of discrete cooling holes around the leading edge of a blunt body that is subjected to periodically incoming wakes as well as free-stream turbulence with various levels of intensity. The cooling holes have a configuration similar to that of typical turbine blades except for the spanwise inclination angle. Secondary air is heated so that the temperature difference between the mainstream and secondary air is about 20 K. In this case, the air density ratio of the mainstream and secondary air becomes less than unity, therefore the flow condition encountered in an actual aero-engine cannot be simulated in terms of the density ratio. A spoke-wheel type wake generator is used in this study. In addition, three types of turbulence grids are used to elevate the free-stream turbulence intensity. We adopt three blowing ratios of the secondary air to the mainstream. For each of the blowing ratios, wall temperatures around the surface of the test model are measured by thermocouples situated inside the model. The temperature is visualized using liquid crystals in order to obtain qualitative information of film effectiveness distribution.


Author(s):  
K. Funazaki ◽  
M. Yokota ◽  
S. Yamawaki

Detailed studies are conducted on film effectiveness of discrete cooling holes around the leading edge of a blunt body that is subjected to periodically incoming wakes as well as free-stream turbulence with various levels of intensity. The cooling holes have a configuration similar to that of typical turbine blades except for the spanwise inclination angle. Secondary air is heated so that the temperature difference between the mainstream and secondary air is about 20K. In this case, air density ratio of the mainstream and secondary air becomes less than unity, therefore the flow condition encountered in an actual aero-engine can not be simulated in terms of the density ratio. A spoke-wheel type wake generator is used in this study. In addition, three types of turbulence grids are used to elevate the free-stream turbulence intensity. We adopt three blowing ratios of the secondary air to the mainstream. For each of the blowing ratios, wall temperature around the surface of the test model are measured by thermocouples situated inside the model. The temperature is visualized using liquid crystals in order to obtain qualitative information of film effectiveness distribution.


Author(s):  
Ranjan Saha ◽  
Jens Fridh ◽  
Torsten Fransson ◽  
Boris I. Mamaev ◽  
Mats Annerfeldt

An experimental study of the hub leading edge contouring using fillets is performed in an annular sector cascade to observe the influence of secondary flows and aerodynamic losses. The investigated vane is a three dimensional gas turbine guide vane (geometrically similar) with a mid-span aspect ratio of 0.46. The measurements are carried out on the leading edge fillet and baseline cases using pneumatic probes. Significant precautions have been taken to increase the accuracy of the measurements. The investigations are performed for a wide range of operating exit Mach numbers from 0.5 to 0.9 at a design inlet flow angle of 90°. Data presented include the loading, fields of total pressures, exit flow angles, radial flow angles, as well as profile and secondary losses. The vane has a small profile loss of approximately 2.5% and secondary loss of about 1.1%. Contour plots of vorticity distributions and velocity vectors indicate there is a small influence of the vortex-structure in endwall regions when the leading edge fillet is used. Compared to the baseline case the loss for the filleted case is lower up to 13% of span and higher from 13% to 20% of the span for a reference condition with Mach no. of 0.9. For the filleted case, there is a small increase of turning up to 15% of the span and then a small decrease up to 35% of the span. Hence, there are no significant influences on the losses and turning for the filleted case. Results lead to the conclusion that one cannot expect a noticeable effect of leading edge contouring on the aerodynamic efficiency for the investigated 1st stage vane of a modern gas turbine.


Author(s):  
Patrick H. Wagner ◽  
Jan Van herle ◽  
Lili Gu ◽  
Jürg Schiffmann

Abstract The blade tip clearance loss was studied experimentally and numerically for a micro radial fan with a tip diameter of 19.2mm. Its relative blade tip clearance, i.e., the clearance divided by the blade height of 1.82 mm, was adjusted with different shims. The fan characteristics were experimentally determined for an operation at the nominal rotational speed of 168 krpm with hot air (200 °C). The total-to-total pressure rise and efficiency increased from 49 mbar to 68 mbar and from 53% to 64%, respectively, by reducing the relative tip clearance from 7.7% to the design value of 2.2%. Single and full passage computational fluid dynamics simulations correlate well with these experimental findings. The widely-used Pfleiderer loss correlation with an empirical coefficient of 2.8 fits the numerical simulation and the experiments within +2 efficiency points. The high sensitivity to the tip clearance loss is a result of the design specific speed of 0.80, the highly-backward curved blades (17°), and possibly the low Reynolds number (1 × 105). The authors suggest three main measures to mitigate the blade tip clearance losses for small-scale fans: (1) utilization of high-precision surfaced-grooved gas-bearings to lower the blade tip clearance, (2) a mid-loaded blade design, and (3) an unloaded fan leading edge to reduce the blade tip clearance vortex in the fan passage.


Author(s):  
Ranjan Saha ◽  
Boris I. Mamaev ◽  
Jens Fridh ◽  
Björn Laumert ◽  
Torsten H. Fransson

Experiments are conducted to investigate the effect of the pre-history in the aerodynamic performance of a three-dimensional nozzle guide vane with a hub leading edge contouring. The performance is determined with two pneumatic probes (5 hole and 3 hole) concentrating mainly on the endwall. The investigated vane is a geometrically similar gas turbine vane for the first stage with a reference exit Mach number of 0.9. Results are compared for the baseline and filleted cases for a wide range of operating exit Mach numbers from 0.5 to 0.9. The presented data includes loading distributions, loss distributions, fields of exit flow angles, velocity vector and vorticity contour, as well as, mass-averaged loss coefficients. The results show an insignificant influence of the leading edge fillet on the performance of the vane. However, the pre-history (inlet condition) affects significantly in the secondary loss. Additionally, an oil visualization technique yields information about the streamlines on the solid vane surface which allows identifying the locations of secondary flow vortices, stagnation line and saddle point.


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