Performance Analysis and Aerodynamic Design of Axial Flow Compressors

الملخص

The main objective of the paper is to analyze the
performance of axial flow compressors and to generate a
systematic design approach which enables to design
subsonic flow ones. In order to investigate the validity of this
approach, the LP axial flow compressor of the RR Spey
MK511 turbofan engine is taken as an example. The design
calculations were based on thermodynamics, gas dynamics,
fluid mechanics and empirical relations. The flow is
assumed to be of two-dimensional compressible type with
constant axial and rotor blade velocities with a free-vortex
swirl distribution. Design calculations include
thermodynamic properties of the working fluid, number of
compressor performance parameters such as, stage
temperature rise and number, flow and blade angles (blade
twist), velocity triangles and relative inlet Mach number at
rotor blades tips as well as blades tip and hub diameters. A
repeated calculation is made to determine these parameters
along compressor stages. The variation of velocity whirl
components, air and blade angles, deflection and degree of
reaction from root to tip of the blades were also determined.
The twist of the blades along the blade length is set
according to the recommended values in order to obtain
smooth blade twist profile.