Surge/ stall study on the compressor of a mini jet engine

• Main Author: Tan, Xiangwei
• Other Authors: Tang Hui
• Format: Final Year Project
• Language: English
• Published: 2014
• Subjects: DRNTU::Engineering::Aeronautical engineering::Aerodynamics
• Online Access: http://hdl.handle.net/10356/60082
• Institution: Nanyang Technological University

A Computational Fluid Dynamics (CFD) framework was established to analyse the flow within the SR-30 mini jet engine compressor. The software utilized in the study were ANSYS ICEM CFD and FLUENT. The simulations adopted the Multiple Reference Frame (MRF) model for steady flow. Preliminary simulation was conducted with a coarse mesh of 400,000 cells to achieve first order transient solution based on the Spalart-Allmaras turbulence model. Results from the investigation indicated that the total pressure of the compressor increases from the inlet to outlet. The pressure was found to be the highest at the transition region between the impeller and diffuser blades. However, the static pressure unexpectedly decreases along the diffuser blades to the lowest at the outlet guiding vane. The velocity vector plot showed no swirling or flow separation. In addition, studies also showed positive correlation between total pressure ratio and impeller rotational velocity as well as mass flow rates. Pressure output of the SR-30 compressor can be maximized by operating at high impeller rotational speed and at relatively low mass flow rate.