Shell structure for flame tube of aircraft engine

Abstract

The invention relates to a shell structure for a flame tube of an aircraft engine. The shell structure comprises a reinforcing ring of a shell of the flame tube, a fixed ring, a fixed hook, a front air inlet cone, a front section of the shell of the flame tube, an air inlet hopper, a rear section of the shell of the flame tube and a rear mounting edge of the flame tube, wherein the front section of the shell of the flame tube and the rear section of the shell of the flame tube are connected into a whole by welding so as to form the shell of the flame tube, and the reinforcing ring of the shell of the flame tube is welded at the front end of the front section of the shell of the flame tube so as to form an inner mounting edge of the front air inlet cone. The rear mounting edge of the flame tube is welded at the rear end of the rear section of the shell of the flame tube; the air inlet hopper is welded in a long circular hole punched at the front section of the shell of the flame tube; the fixed hook is welded on the front air inlet cone; and the width of the fixed hook is changed from the original 11mm to 4.5mm, the thickness of the fixed hook is changed from 1.8mm to 3mm, the placement angle of the fixed hook is changed to the placement along the direction of air flow, and an included angle between the fixed hook and the radial axial line of the flame tube is 30 degrees. The shell structure can effectively reduce the temperature on the wall surface of the shell of the flame tube; and excess materials on the gasward side surface of the air inlet hopper can be cut off, and the problem of occurrence of cracks on the air inlet hopper can be solved.

Description

technical field [0001] The invention relates to a shell structure of an aero-engine flame tube, in particular to an improved design of the flame tube shell for improving the service life of the aero-engine. The invention belongs to the technical field of structural design of an aero-engine combustor. Background technique [0002] The hottest spot of the original flame tube of the existing aero-engine is on the side of the air intake funnel. After a long period of operation under heavy load, cracks often appear, and the cracks expand and cause pieces to fall, which endangers the normal operation of the engine rotor system, affects the service life of the engine, and endangers the safety of the engine. . In order to meet the performance requirements of the turbojet-11 aero-engine from the engine user and improve the service life of the engine, the design of the flame tube casing of this type of aero-engine has been improved. The shell of the original flame tube is the weakes...

AI Technical Summary

Problems solved by technology

The shell of the original flame tube is the weakest link of this type of engine. Due to structural design defects, the temperature distribution on the wall of the flame tube shell is very uneven, with a maximum temperature difference of over 400°C. After operation, cracks often appear, and the cracks extend to the small hole between the two air intake hoppers, which is prone to blockage and affects the working life of the whole machine

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