Affiliation:
1. Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, China
2. Collaborative Innovation Center of Advanced Aero-Engine, Beijing, China
Abstract
To investigate the effect of high-temperature steam ingestion on the aerodynamic stability of a transonic axial compressor, a NASA Rotor 37 was numerically simulated. The effects of the high-temperature steam mass fraction, the temperature rise rate, the maximum temperature, and the distribution of steam at the inlet boundary on the aerodynamic stability of a transonic axial rotor were investigated, using the steady-state and quasi-steady methods. From the simulation results, it was found that high-temperature steam ingestion has an adverse effect on the transonic rotor. The greater the steam mass fraction and the maximum temperature, the greater the impact of the steam ingestion on the stability boundary. The temperature rise rate has little effect on the performance and stability. The distribution of steam at the inlet boundary has a significant impact on the performance and stability. In addition, with the ingestion of high-temperature steam, the average density of the gas at the rotor inlet is affected, and the passage shock position moves forward at the same time, which leads to the occurrence of the stall in advance.
Subject
Mechanical Engineering,Aerospace Engineering
Cited by
3 articles.
订阅此论文施引文献
订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献