text: The axial flow compressor consists of altet- 
  nate rows of rotating and stationary airfoils. 
  The major components of the axial flow com- 
  pressor ate illustrated in figure 2.7. A pressure 
  rise occurs through the row of rotating blades 
  since the airfoils cause a decrease in velocity 
  relative 
  rise takes place through the row of stationary 
  blades since these airfoils cause a decrease in 
  the absolute velocity of flow. The decrease 
  I in velocity, relative or absolute, eEeLts a com- 
  1 ptession of the flow and causes the increase in 
  the pressure rise pet 
  static pressure. While 
  stage of the axial compressor is relatively Jo%-, 
  the efficiency is very high and high pressure 
  ratios can be obtained efficiently by successive 
  axial stages. Of course, the eficient pressure 
  rise in each stage is limited by excessive gas 
  velocities. The multistage axial flow com- 
  pressor is capable of providing pressure ratios 
  
  to  the blades. Additional pressure 
  
  While the combustion chamber design may 
  .take various forms and configurations, 
  the 
  main features of a typical combustion chamber 
  ate illustrated by figure 2.8. The combustion 
  chamber receives the high pressure discharge 
  from the compressor and introduces apptoxi- 
  mately one half of this air into the immediate 
  area of the fuel spray. This primary combus- 
  tion air must be introduced with 
  relatively 
  turbulence and quite low velocities to 
  high 