The stability

reliability and performance of two spool turbojet engine will be affected by the matching correlation between 1st and 2nd turbine nozzle areas and engine nozzle area.An analysis method is presented in this paper based on six equations which are easy to apply.A programme of constant low pressure turbine power is adopted to replace the programme of constant low pressure rotor speed.The parameters measured on the engine test bed are used to define component parameters.The calculation was conducted only at design rotational speed.The computation results were used to guide the triarea adjustment of a new developed engine and attained the suitable triarea adjustment range.The engine based on this programme and adjustment is proved to be stable and reliable in flight.