Abstract
An improved integral method is proposed and developed for the quantitative prediction of distorted inlet flow propagation through axial compressor. The novel integral method is formulated using more appropriate and practical airfoil characteristics, with less assumptions needed for derivation. The results indicate that the original integral method (Kim et al., 1996) underestimated the propagation of inlet flow distortion. The effects of inlet flow parameters on the propagation of inlet distortions as well as on the compressor performance and characteristic are simulated and analyzed. From the viewpoint of compressor efficiency, the propagation of inlet flow distortion is further described using a compressor critical performance and its associated critical characteristic. The results present a realistic physical insight to an axial-flow compressor behavior with a propagation of inlet distortion.
Highlights
Compression system is an important component of the gas turbine engine, and its performance strongly influences the performance of all other components
By using the newly developed integral method, an investigation is proceeded to present the effects of inlet parameters upon the downstream flow features with inlet distortion, including the inlet distortion propagation, the compressor critical performance and critical characteristic
The most significant part in the current effort is the development of the application with airfoil characteristics
Summary
Compression system is an important component of the gas turbine engine, and its performance strongly influences the performance of all other components. Distorted inlet flow in axial compressor may cause the component mismatch and instability problems, such as rotating stall or even surge, or a combination of them, which might result in catastrophic damage to the entire engine. In order to rapidly predict the distorted performance and distortion attenuation of an axial compressor without using comprehensive CFD codes and parallel supercomputer, it is necessary to make some simplifications, and some elegance and detail of flow physics must be sacrificed. The integral method provided a useful physical insight about the performance of the axial compressor with an inlet flow distortion. By using the newly developed integral method, an investigation is proceeded to present the effects of inlet parameters upon the downstream flow features with inlet distortion, including the inlet distortion propagation, the compressor critical performance and critical characteristic.
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