Non-linear dynamic performance of rotor–bearing systems supported by plain journal bearings strongly depends on the mathematical oil film force model. In this article, the analytical solution of oil film pressure for finite length plain journal bearing is obtained by employing the separation of variables method to analytically solve the Reynolds equation based on dynamic Gümbel boundary conditions. The analytical expression of oil film force is then derived by applying the integral method. The expression of the pressure is analysed to investigate the pressure distribution. The oil film force of the analytical model is compared with the results from other methods, namely, long bearing approximation, short bearing approximation, as well as the finite difference method. The results clearly validate the current model. The proposed model also proved to be efficient for analysing the dynamic characteristics of a rigid rotor supported by plain journal bearings.
The nonlinear dynamic characteristics of rotating ramjet rotor supported by hybrid gas bearing are studied. The compression inlet flow field at different back pressure levels is analyzed and the normal working back pressure level is determined. The periodic movement phenomenon of normal shock wave in compression inlet is presented. The influence on the compression inlet flow field with the variation of structure dimension is introduced. Then, the nonlinear compression inlet flow force generated from the whirling of the rotor is obtained. The model for the rotating ramjet rotor supported by the hybrid gas bearing is established by the finite element method. The equation of motion for the rotating ramjet rotor is numerically solved and coupled with the gas lubricated Reynolds equation considering the time terms. The vibration characteristics of the rotating ramjet with different supply pressure and unbalanced mass eccentricities are solved by the Newmark method. The orbit trajectory diagram, frequency spectrum diagram, and time response diagram are obtained. Then, the stability of the rotating ramjet rotor system is discussed. The results indicate that the compression inlet is under the condition of high adverse pressure gradient, the shock wave, expansion wave, reflections and crossings of the shock waves, boundary layer–shock wave interference, and separation of the flow, which lead to the unstable flow of the compression inlet. The nonlinear compression inlet flow force can cause sub-synchronous vibration. If the supply pressure and eccentricities are properly designed, the vibration amplitudes can be decreased and the stability will be improved, which will make the foundation for the vibration control of the rotating ramjet system.
A unique supersonic compressor rotor with high pressure ratio, termed the Rampressor, is presented by Ramgen Power Systems, Inc. (RPS). In order to obtain the excitation characteristic and performance of Rampressor inlet flow field under external excitation, compression inlet flow of Rampressor is studied with considering Rampressor rotor whirling. Flow excitation characteristics and performance of Rampressor inlet are analyzed under different frequency and amplitude of Rampressor rotor whirling. The results indicate that the rotor whirling has a significant effect for flow excitation characteristics and performance of Rampressor inlet. The effect of rotor whirling on the different inlet location excitation has a definite phase difference. Inlet excitation becomes more complex along with the inlet flow path. More frequency components appear in the excitation spectrum of Rampressor inlet with considering Rampressor rotor whirling. The main frequency component is the fundamental frequency, which is caused by the rotor whirling. Besides the fundamental frequency, the double frequency components are generated due to the coupling between inlet compression flow of Rampressor rotor and rotor whirling, especially in the subsonic diffuser of Rampressor rotor inlet. With the increment of rotor whirling frequency and whirling amplitude, the complexity of Rampressor inlet excitation increases, and the stability of Rampressor inlet performance deteriorates.
A unique supersonic compressor rotor with high pressure ratio, termed the Rampressor, is presented by Ramgen Power Systems, Inc., (RPS). Based on the models of Rampressor inlet, the inlet flow field with bleed system is numerically studied. Validation of the employed computational fluid dynamics (CFD) scheme is provided through test cases. The effects of boundary layer bleed location and bleed amount on Rampressor rotor inlet start and flow performance are analyzed. The results indicate that the boundary layer bleed has a significant effect for start and flow performance of Rampressor inlet. Bound ary layer bleed technique has been applied to eliminate the emerging flow separation zone for enhancing Rampressor rotor inlet performance and enlarging its stable working range. The starting ability and flow performance of Rampressor inlet are efficiently improved by bleeding system, but the improvement effect is different for Rampressor inlet with different bleed location. Along the position of bleeding system moves forward, the range of Rampressor inlet normal work rotation speed is enlarged. The flow performance of Rampressor inlet improves obviously with the increment of bleed flow rate, and exit stability of Rampressor inlet enhances. And in the same back pressure work condition of Rampressor inlet, bleed system has been shown to be effective that exit stability of Rampressor inlet ameliorates, but the loss of compressed air from the bleed system has a negative effect on overall Rampressor inlet efficiency.
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