The author modified the Abu-Ghannam and Shaw Transition Model (AGS Transition Model) with ready test data,set out the concept of calculating the transition length with arc Reynolds number and compared the calculated value with the test value.

Through the forming analysis of the deep-trough belt conveyor transition section, this paper gives the calculating method of the transition length according to the allowable belt strain and specific elongation.

Considering double-layer structure adopted commonly in marine pipeline at present, the transition length of double-layer pipeline is calculated by integral equivalent method in this paper, and calculating equation of transition length is deduced according to the above method.

The theory and method of waves generated by serpent-type wavemakers are described in this paper. The transition length in front of the wave boards is determined by experiments. The properties of the generated waves are studied experimentally and the results of the regular waves are compared with the theoretical values.

The distance from the entrance required for practically complete transition has been calculated by Boussiuesq and olso by Schiller, and formulas for calculating tle transition length have been proposed.

An attempt is thus made, in this paper, to calculate this lenqth by applying Schiller's theory; and the result obtained is given by L=0.0259bR in which L is the transition length, b is half the distance between the plates and R is the Reynolds number.

Moreover, transition length is correlated with a shape parameter.

Small fatigue cracks (≈30-Μm long) were naturally initiated from smooth specimens and grown past the transition length (≈200 Μm), where they exhibited the characteristics of large fatigue cracks.

The influence of the transition decreases with decreasing transition length and increasing ratio of the maximum radius to the minimum radius of the transition.

The influence of a mechanical obstacle placed at the end of the transition zone on the stabilization of the detonation starting point and the shortening of the transition length is investigated.

The transition length for the cases of the plate-wake were shorter than those for the cases of the cylinder-wake as well as the uniform flow.

It has long been realised that for laminar flow through a circuclar pipe, the Poiseulle's velocity distribution exits only at a sufficient distance downstream from the entrance to the pipe. For a well-rounded entrance, the velocily distribution at the entrance is approximately uniform, it then varies gradually with the distance from the entrance until the parabolic distribution is fully developed. The distance from the entrance required for practically complete transition has been calculated by Boussiuesq and...

It has long been realised that for laminar flow through a circuclar pipe, the Poiseulle's velocity distribution exits only at a sufficient distance downstream from the entrance to the pipe. For a well-rounded entrance, the velocily distribution at the entrance is approximately uniform, it then varies gradually with the distance from the entrance until the parabolic distribution is fully developed. The distance from the entrance required for practically complete transition has been calculated by Boussiuesq and olso by Schiller, and formulas for calculating tle transition length have been proposed. For laminar flow between parallel plates, however, no information for the length of transition appears to be available. An attempt is thus made, in this paper, to calculate this lenqth by applying Schiller's theory; and the result obtained is given by L=0.0259bR in which L is the transition length, b is half the distance between the plates and R is the Reynolds number.

A novel finline transition structure is presented in this paper. The basic configuration takes the form of a wedge-shaped notch cut in the finline substrate along the finline longitudinal axis. The wedge-shaped notch together with the finline taper provides a impedance match between the air-filled waveguide and finline. The optimal depths of the wedge-shaped notch for different tapered transition lengths have been determined by trial and error. About a 10-dB improvement in return loss has been obtained...

A novel finline transition structure is presented in this paper. The basic configuration takes the form of a wedge-shaped notch cut in the finline substrate along the finline longitudinal axis. The wedge-shaped notch together with the finline taper provides a impedance match between the air-filled waveguide and finline. The optimal depths of the wedge-shaped notch for different tapered transition lengths have been determined by trial and error. About a 10-dB improvement in return loss has been obtained over most of the X-band as compared with the ordinary tapered transition structure.

Several problems involved in the prediction of heat transfer coefficient on the turbine blade profiles without film cooling are studied in this paper for the purpose of improving the accuracy.These problems are:heat transfer in the vicinity of stagnation point,the location of boundary layer transition,heat transfer of transitional boundary layer and the influence of free stream turbulence intensity.Cebeci Smith method is used to solve the ...

Several problems involved in the prediction of heat transfer coefficient on the turbine blade profiles without film cooling are studied in this paper for the purpose of improving the accuracy.These problems are:heat transfer in the vicinity of stagnation point,the location of boundary layer transition,heat transfer of transitional boundary layer and the influence of free stream turbulence intensity.Cebeci Smith method is used to solve the boundary layer equations obtaining the similar solution in the vicinity of stagnation point.It is assumed that the free stream velocities near the leading edge of a blade can approximately be expressed as that for a cylinder,the radius of which equals to that of leading edge circle or to the radius of a“equivalent cylinder”,the solution obtained by this method in the vicinity of stagnation point is used as a initial profiles of velocity and enthalpy for the computation of boundary layer along the blade surface.STANS [9] with some modifications is used to calculate heat transfer coefficient on the rest part of the blade surface.Transition origin and transition length are predicted by using the models suggested by Seyb [5] and Dhawn at el. [12] respectively.In order to take the free stream turbulence intensities into account,a turbulence viscosity is introdued as a part of effective viscosity of the fluid.Several numerical examples obtained by the proposed method in this paper indicate better agreement with the experimental data than by original STAN 5.