Afterburning Turbojet Engines
The term afterburning, or reheat, applies to engines in which a second
combustor is placed between stations 5 and 7 (see Fig. 1.7) to increase the
temperature of the gas downstream of the turbines that drive the compressors.
Afterburners are stationary and are consequently subject to far less
stress than turbine rotors. The metal parts are much more easily cooled
than turbine airfoils and stoichiometric temperatures can thus be approached
unless unwanted disassociation intervenes. Engine thrust can be
augmented by about 50% at takeoff and by over 100% at high speeds. If
we again assume constant specific heat, the output specific energy may be
expressed as
The term afterburning, or reheat, applies to engines in which a second
combustor is placed between stations 5 and 7 (see Fig. 1.7) to increase the
temperature of the gas downstream of the turbines that drive the compressors.
Afterburners are stationary and are consequently subject to far less
stress than turbine rotors. The metal parts are much more easily cooled
than turbine airfoils and stoichiometric temperatures can thus be approached
unless unwanted disassociation intervenes. Engine thrust can be
augmented by about 50% at takeoff and by over 100% at high speeds. If
we again assume constant specific heat, the output specific energy may be
expressed as
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