Unsteady Numerical Simulation in a Supersonic Compressor Cascade with a Strong Shock Wave
-
Shaowen Chen
,
Qinghe Meng
Abstract
The most important flow behaviour of supersonic compressor cascades is the shock wave boundary layer interaction (SWBLI). Large eddy simulation (LES) and multiple analysing methods are applied in current study to capture more details of the flow field. It is noted that the LES can catch the dual peaks feature near the SWBLI region with respect to the experimental results. Besides, SWBLI is not only the main losses source in the cascade, but also the most important origin of the unsteadiness behaviour. The high frequency signals correspond to the coherent structure in the boundary layer and dissipate downstream in the cascade, while the low frequency signals relate to the motion of the reflection point of the passage oblique shock wave and dominate the frequency spectrum downstream.
Funding statement: This study is financially supported by National Natural Science Foundation of China (Grant No. 51776048 and 51436002).
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Articles in the same Issue
- Frontmatter
- Review
- Assessment of Exit Temperature Pattern Factors in an Annular Gas Turbine Combustor: An Overview
- Original Research Articles
- Optimization of Trenched Film Cooling Using RSM Coupled CFD
- Modeling of Relative Exergy Destruction for Turboprop Engine Components Using Deep Learning Artificial Neural Networks
- Direct Thrust Inverse Control of Aero-Engine Based on Deep Neural Network
- Entropy, Energy and Exergy for Measuring PW4000 Turbofan Sustainability
- A Centrifugal Compressor Performance Map Empirical Prediction Method for Automotive Turbochargers
- Unsteady Numerical Simulation in a Supersonic Compressor Cascade with a Strong Shock Wave
- CFD Study of Combined Impingement and Film Cooling Flow on the Internal Surface Temperature Distribution of a Vane
- CFD Analysis of Flow and Performance Characteristics of a 90°curved Rectangular Diffuser: Effects of Aspect Ratio and Reynolds Number
- Effects of the Recess Length of the Pilot Stage on the Lean Blowout Limits for the Multipoint Lean Direct Injection Combustors
- Stress and Vibration Analysis of a PDC (Pulse Detonation Chamber)
- Transverse Injection Experiments within an Axisymmetric Scramjet Combustor
