Aero-engine annular flame barrel array inclined hole flanging die and using method thereof

Abstract

The invention discloses an aero-engine annular flame barrel array inclined hole flanging die and a using method thereof. The aero-engine annular flame barrel array inclined hole flanging die comprisesan upper die base and a lower die base which are matched, an upper die and a lower die are arranged between the upper die base and the lower die base, and a plurality of die sets matched with array inclined holes are arranged between the upper die and the lower die in the circumferential direction; a die assembly is characterized in that a workpiece is placed between the upper die and the lower die, a male die ejection device is arranged between the lower die and the lower die base, and a wedge and a second spring which are connected are arranged between the upper die base and the upper die;and the upper die base, the upper die, the lower die and the lower die base are provided with guide holes with the inclined angle the same as the inclined angle of the array inclined holes in the circumferential direction of the head of an aero-engine annular flame barrel. The problem that flanging cannot be carried out on flanging holes which are not coincident in annular workpiece shaft direction is solved, flanging of one set of array inclined hole by one die in sequence is achieved, the location degree of the flanging holes is improved, and the production efficiency is imporved.

Description

technical field [0001] The invention belongs to the technical field of aviation manufacturing; in particular, it relates to an aero-engine annular flame tube array oblique hole flanging mold and a use method thereof. Background technique [0002] The new axial-flow aviation turbofan engine uses an annular flame tube. In order to ensure the uniformity of the temperature field at the outlet of the flame tube, a number of small vortex devices are evenly distributed on the outer circumference of the flame tube head, and a fuel nozzle is installed in the center of each vortex device. In order to stabilize combustion and ensure the aerodynamic requirements of the flame tube, the axis of the vortex usually forms a certain angle with the axis of the engine. The inner and outer walls of the flame tube are bridged together through the head transition section, and the vortexers are evenly installed on the head transition section. The position and direction of the vortex device are det...

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Problems solved by technology

[0004] The invention provides an aero-engine annular flame tube array oblique hole flanging mold and its use method, which solves the problem that the flanging holes in the circular workpiece axis direction cannot be flanging at the same time, and realizes that a set of molds can complete a set of molds sequentially. The flanging of the array of oblique holes improves the position of the flanging holes and improves production efficiency

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