[wael_moto]

Air at temperature of 290K enters a ten stage axial flow compressor at the rate of 3kg/s.
the pressure ratio is 6.5 and the isentropic efficiency is 90%, the compression process being adiabatic.
The compressor has symmetrical blades.
The axial velocity of 110 m/s is uniform and the peripheral speed of each stage is 180 m/s.
determines the rotor and stator blade angles and flow angles and also the power given to the air.
Assume temperature change in each stage is constant.

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هذه
https://gymkhana.iitb.ac.in/~scp/scp...bines/tut1.pdf

أو هذه

https://nptel.ac.in/content/storage2.../TutLec-05.pdf


https://www.academia.edu/6332238/Axial_Flow_Compressors

Problem#2 In an axial flow compressor air enters the compressor at stagnation conditions of 1 bar and 290 K. Air enters with an absolute velocity of 145 m/s axially into the first stage of the compressor and axial velocity remains constant through the stage. The rotational speed is 5500 rpm and stagnation temperature rise is 22 K. The radius of rotor-blade has a hub to tip ratio of 0.5. The stage work done factor is 0.92, and the isentropic efficiency of the stage is 0.90. Assume for air Cp-1005 kJ/(kg·K) and y= 1.4 Determine the followings. List your assumptions. (i) The tip radius and corresponding rotor angles at the tip, if the inlet Mach number for the relative velocity at the tip is limited to 0.96. (ii) The mass flow at compressor inlet (ii) The stagnation pressure ratio of the stage and power required by the first stage. (iv) The rotor angles at the root section.

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https://www.docsity.com/en/test-pape...er-2010/33270/