HIGH BYPASS TURBOFAN ENGINE PERFORMANCE: INTAKE PRESSURE RECOVERY EFFECT

Document Type : Original papers

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Mechanical Engineering Departement. Faculty of Engineering, Al-Baha University KSA, on Leave from Institute of Aviation Engineering and Technology, Giza, Egypt, eslam@bu.edu.sa.

Abstract

The aviation industry continues to innovate onboard systems to enhance efficiency. This research examines the role of engine intake performance, specifically pressure recovery (PR), in improving the performance of a three-spool turbofan engine. Variations in an aircraft's flight path have a direct impact on pressure recovery. A computational fluid dynamics (CFD) model was first developed to assess pressure recovery at various angles of attack (0°, 10°, 20°, 30°, and 40°) at a Mach number of 0.82 and an altitude of 12,000 meters. Using ANSYS FLUENT® 19 with the Spalart-Allmaras turbulence model, the simulations revealed that the pressure recovery is highest at lower angles and gradually decreases at higher angles, with values between 0.92 and 0.98. MATLAB was then employed to analyze how intake pressure recovery affects the performance of a three-spool turbofan engine under similar conditions, with a Mach number range from 0.2 to 1. The results showed that improved pressure recovery led to a 4% enhancement in specific thrust, a 3% reduction in thrust-specific fuel consumption, and overall gains in engine efficiency. The study suggests that maintaining high pressure recovery is crucial to optimizing engine performance.

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