Investigation On Rotor/Stator Interface Processing Method And Analysis On Configuration And Aerodynamic Of Tubine

This paper consists of two parts. The frist part is the investigation on rotor/stator interface processing method. The processing method of the rotor/stator interface is the key in numerical simulation of turbomachinery. To improve the precision and efficiency of turbomachinery simulation, it's of great important to investigate the influence of different interface processing method to the simulation result. In the past twenty years, researchers gave series of approach to simulate the interface, which was extendly used in various CFD software. This dissertation is aimed towards comparing the computing result of different rotor/stator interface processing method, providing reference for the choice of interface processing method in turbomachinery numerical simulation.For the sake of realization research purpose above, this dissertation is organized as follow:1) As the theories foundation of whole dissertation, sever different approaches, such as mixing plane, frozen rotor, sliding plane are introduced in detail.2) Take advantage of fast speed of 2d numerical simulation, flow field of middle section of turbine blade is simulated, and apply different approaches to simulate the rotor/stator interface. Result show that when apply mixing plane method, flow turning angle and total pressure recovery coefficient are bigger than sliding plane method. The difference of result becomes larger when the gap and translation speed turn small.3) The detailed numerical simulation on a ram turbine is done, anaysis the influence of different rotor/stator interface processing method to numerical result of the tubine's overall performance. The result show that interface treatment have no significant effect on flow mass and total pressure ratio, but have certain effect on stage efficiency. The faster the rotation speed, the larger the difference of effciency. Especially when working state is located near the instability boundary, the difference became even larger.4) Take the NASA STAGE35 as study object, anaysis the influence of different rotor/stator interface treatment to numerical result of the compressor's overall performance. Study imply that when the interface is simulate by frozen rotor or sliding plane method, the numerical result agreed well with experimental test data for overall performance than mixing plane method. When take mixing plane method to simulate interface, the efficiency is biger than test data, and the tatal pressure ratio is smaller than test data. In addition, the difference of numerical result of different interface treatment becomes larger, when the flow mass and rotating speed become low.Through the above research, we find that the rotor/stator interface treatment have no significant effect on the numerical result of turbine. The steady computation,which uses mixing plane method to simulate the interface, not only can get the precision as unsteady computation, but also calculate fast. On the other hand, the rotor/stator interface treatment has a great influence on the numerical result of the compressor. Making use of frozen rotor model to simulate the interface, the precision is high than mixing plane, and the computation speed is faster than sliding plane.The second part of thi.s paper is the analysis of configuration and aerodynamic character. In the paper, a new algorithm is applied to calculate the geometric parameters of blade profile according to the surveying data of the blade profile. Fristly, reviews cubic spline curve of interpolation on the surveying data, then obtain the central arced curve of the blade section, correct the central arced curve with least square method, at last calculate various geometric parameters of the blade. By solving the geometric parameters of a ram tubine, feasibility of the algorithm is validated.