text: Suppose that the fuel flow is increased be- 
  yond the steady state requirement without a 
  change in rotative speed. The increased com- 
  bustion chamber pressure due to the greater 
  the compressor dis- 
  fuel flow requires that 
  charge pressure be higher. For the instant 
  before an engine speed change occurs, an in- 
  crease in compressor discharge pressure will be 
  accompanied by a decrease in compressor flow 
  velocity. The equivalent effect is illustrated 
  by the flow components onto the rotating com- 
  pressor blade of figure 2.13. One component 
  of velocity is due to rotation and this compo- 
  nent remains unchanged for a given rotative 
  velocity of the single blade. The axial flow 
  velocity for steady state operation combines 
  with rotational component to define a result- 
  ant velocity and direction. 
  If the axial flow 
  component is reduced, the resultant velocity 
  and direction provide an increase in angle of 
  
  A gross overstress or overtemperature of the 
  is 
  turbine section will produce damage that 
  immediately apparent. However, the creep 
  and fatigue damage accumulated through pe- 
  riods of less extreme’ overstress or overtem- 
  turbine is 
  perature is more subtle. 
  sibject to repeated excessive temperatures, the 
  increased rate of creep and fatigue 
  greatly 
  the 
  damage wiIl produce failure early within 
  anticipated service life. 
  
  If  the 
  
  Generally, 