Multi-stage compressor modeling method and system

Abstract

The invention provides a multi-stage compressor modeling method and system. The method comprises the following steps: a model amplification step: amplifying an original model to obtain an amplification model; a friction factor correction step: correcting a friction factor of the amplification model by resetting the rotating speed to ensure that the ratio of the friction loss in the total loss is unchanged; a diffusion factor correction step: correcting the diffusion factor of the amplification model by resetting each stage of moving and static blades, and ensuring that the diffusion factors of outlets of each stage of moving blades are consistent; a clearance correction step: correcting the clearance loss of the amplification model by resetting the blade tip clearance to ensure that the ratio of the clearance loss in the total loss is unchanged; a use method step: carrying out pneumatic experiment and test based on the amplification model, and carrying out pneumatic performance analysis on the original model. According to a high-pressure stage amplification model of a multi-stage gas compressor, the flow field and the prototype have very high similarity, so that it is guaranteed that the efficiency, the pressure ratio and the near stall flow are basically equal to those of an original model.

Description

technical field [0001] The present invention relates to the technical field of turbomachinery, in particular to a modeling method and system for a multi-stage compressor. In particular, it preferably relates to a multi-stage compressor high-pressure stage low-speed molding method. Background technique [0002] As one of the three major components of the core engine, the compressor plays an important role in the development of the core engine and the entire engine. In order to improve the performance of the compressor, it is necessary to obtain a detailed flow field of the compressor, conduct an in-depth and detailed analysis of the flow field structure, study the mechanisms of various losses, and propose corresponding improvement plans. However, until now, the detailed flow field inside the high-pressure stage of a compressor is difficult to obtain directly. From an experimental point of view, due to the short blades of the high-pressure stage of the compressor, the small ...

AI Technical Summary

Problems solved by technology

[0005] In view of the related technologies mentioned above, the inventor believes that it is difficult to ensure the same Reynolds number and Mach number at the same time during the actual amplification process of the above method, so the difference in the flow field between the prototype and the modeled compressor is unavoidable

In addition, it is impossible to scale up the dimensions of blade tip clearance and vaneless diffuser, and their differences will inevitably affect the similarity of the flow field

Images