Determination of Surge and Stall Limits of an Axial-flow Turbojet Engine for Control Applications

Ross D. Schmidt · George Vasu · Edward W. McGraw

1953年1月 · National Advisory Committee for Aeronautics

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The data presented are the result of an analysis of oscillograph traces obtained when the engine was operated off steady state by introducing either a step increase or a ramp increase in fuel flow. For a given speed, a lower fuel flow was required for the engine to recover from surge or stall than was necessary for surge or stall to occur. Very little difference existed between the surge line (compressor pressure ratio against engine rotational speed) obtained under transient conditions and that obtained under steady-state conditions by decreasing the flow area with an adjustable first-stage turbine stator.