The invention belongs to the technical field of aero-engine
nozzle design, and particularly relates to an aero-engine
nozzle design method which comprises the following steps: step 1, determining geometric data of sections of an inlet and an outlet of a
nozzle; 2, calculating curvature distribution and total length of sections of an inlet and an outlet of the spray
pipe; 3, determining the initial shapes of other sections outside an inlet and an outlet of the spray
pipe; 4, determining the final shapes of other sections of the spray
pipe; 5, determining the center line geometry of the spray pipe; 6, the positions of an inlet, an outlet and other sections of the spray pipe on the center line are determined; 7, determining geometric coordinates of upper and lower longitudinal lines of the spray pipe; 8, determining a common tangent equation of upper and lower longitudinal lines of the spray pipe; ninthly, determining the geometry of an equal-straight extension section of the outlet of the spray pipe; 10, judging whether the spray pipe meets an omnidirectional shielding condition or not; 11, if the spray pipe does not meet the omni-directional shielding condition, the center line adjusting parameters of the spray pipe are determined; and twelfthly,
iterative design is conducted on the spray pipe till the spray pipe meets the omni-directional shielding condition.