METHOD OF DEBUGGING OF GAS TURBINE ENGINE WITH AFTERBURNER Russian patent published in 2010 - IPC G01M15/00 

FIELD: testing equipment.

SUBSTANCE: invention refers to the field of aeronautical engineering; particularly it refers to debugging of fuel consumption in afterburner of aircraft gas turbine engine. Debugging of gas turbine engine with afterburner is performed by means of debugging of fuel consumption in afterburner. At that turbine outlet temperature and size of exhaust nozzle throat at engine non-augmented power are measured, they are used for determination of required value of exhaust nozzle area at engine augmented power, and debugging of fuel consumption in afterburner is performed by means of action on fuel consumption in afterburner till exhaust nozzle throat comes up to required one. Required value of exhaust nozzle area is determined by formula where F_gf and F_gm are exhaust nozzle areas at augmented power and non-augmented power correspondingly, T_t and T_{f specified} - are measured and specified values of turbine outlet temperature, and augmented and non-augmented powers are performed upon equal operating mode of turbo compressor of gas turbine engine.

EFFECT: debugging of fuel consumption in afterburner under operation conditions.

2 cl, 1 dwg