چكيده به لاتين
Abstract:
Gas turbine engines are one of the major prime movers that are used in the various applications among them, the
industrial power generation in land, marine gas turbines in sea and aero engines in aircrafts propulsion. Due to the
increasing use of airplanes, gas turbines in aircraft engines have a very important position. The axial flow compressors,
as one of the main components of the gas turbines, play a major role in generating the required power.
In the present thesis first of all, by interpreting fluid flow velocity diagrams for each stage specifying the properties
and angles of the blades, inlet and outlet guide vanes, introducing important parameters in the design of multi-stage
axial flow compressors and examining the acceptable range for the selection of each of them by the professors of this
field. Based on laboratory results and practical examples, it has been addressed to the aerodynamic design stages of
this type of compressor with and without the input and output guide vanes.
Afterwards, using the ideals governing the design of high pressure compressors in the air industry, assuming the free
vortex flow and considering the effect of humidity on the performance of each of the stages, based on the inequality
of the axial component of the absolute velocity of the fluid, a program using Excel software for the aerodynamic
design of a thirteen stages axial flow compressor to provide overall total to total pressure ratio of about 17.5 with input
and output guide vanes to achieve the highest amount of mass flow rate per unit area, which is one of the important
goals of designing this type of compressor.
It should be noted that in this program different families of airfoil have been used, with a traditional approach to
selecting suitable rotationary and stationary blades, input and output guide vanes.
Finally, fluid flow velocity diagrams, blade types, geometry, and the angles of blades and vanes (depending on the
type selected), and important parameters in the design, are calculated in each stage and their modifications through
the compressor have been investigated.
Keywords:
Compressor, Axial Flow Compressors, Design Parameters, Aerodynamic Design, Blade Design
