Machining method for reducing deformation of elongated thin-wall rocket combustion chamber shell

A processing method and a technology of a combustion chamber, which are applied to rocket engine devices, jet propulsion devices, machines/engines, etc., can solve problems such as difficulty in bulging and correcting inner braces, and shell instability and depressions.

Inactive Publication Date: 2019-12-31
湖北三江航天江北机械工程有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, for slender and thin-walled shells, it is very difficult to bulge and correct the shape of t...

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0035] For a certain type of combustion chamber shell, the material is D406A ultra-high-strength steel, the length of the cylinder is 850mm, the diameter of the cylinder section is φ200mm, the wall thickness is 1mm, the tensile strength is ≥1620MPa, the elongation is ≥8%, the size and diameter difference is 1mm, and the straightness 0.8mm, the specific processing process is as follows: Step 1) Rough machining of cylindrical blank

[0036] Step 1) Carry out rough machining on the cylindrical blank, remove the surface defect layer, and leave a finishing allowance of 1 mm for the inner hole, outer circle, and end face of the cylindrical blank; in addition, the coaxiality error of the inner hole and outer circle of the cylindrical blank Not more than 0.5mm, and the perpendicularity error between the inner hole, outer circle and both ends of the cylindrical blank is not more than 0.5mm;

[0037] Step 2) quenching and tempering of cylinder billet

[0038] After rough machining, the...

Embodiment 2

[0060] For a certain type of combustion chamber shell, the material is 30CrMnSiA high-strength steel, the length of the cylinder is 3000mm, the diameter of the cylinder section is φ300mm, the wall thickness is 2.2mm, the tensile strength is ≥1040MPa, the elongation is ≥10%, and the diameter difference is 1.5mm. The degree is 1.0mm, and the specific processing process is as follows:

[0061] Step 1) Carry out rough machining on the cylindrical blank, remove the surface defect layer, and leave a finishing allowance of 2mm on one side of the inner hole, outer circle, and end face of the cylindrical blank; in addition, the coaxiality error of the inner hole and outer circle of the cylindrical blank Not more than 0.5mm, and the perpendicularity error between the inner hole, outer circle and both ends of the cylindrical blank is not more than 0.5mm;

[0062] Step 2) quenching and tempering of cylinder billet

[0063] After rough machining, the cylindrical blank is subjected to quen...

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Abstract

The invention discloses a machining method for reducing deformation of an elongated thin-wall rocket combustion chamber shell. The machining method avoids the defects of large deformation and difficult correction of an elongated thin-wall shell caused by quenching and tempering heat treatment after welding of a traditional shell by adopting cylinder heat treatment strengthening, power spinning cold hardening strengthening, laser welding or electron beam welding and stress tempering after welding. By the adoption of the machining method, the size diameter difference and straightness of the shell are remarkably reduced, and design requirements are met without shape correction; for the a shell with the diameter phi of 300 mm, the wall thickness of 2.2 mm and the length of 3,000 mm, the size diameter difference is 1.5 mm and the straightness is 1.0 mm; and for a shell with the diameter phi of 200 mm, the wall thickness of 1 mm and the length of greater than 800 mm, the size diameter difference is 1 mm, and the straightness is 0.8 mm.

Description

technical field [0001] The invention belongs to the technical field of solid rocket combustor casing processing, and in particular relates to a processing method for reducing the deformation of a slender and thin-walled rocket combustor casing. Background technique [0002] The solid rocket motor is the power device of the aerospace vehicle, which is composed of the main parts such as the combustion chamber, the propellant grain, the nozzle, and the igniter. The combustor shell is a key part of the solid rocket motor system, which provides power for the aircraft through the combustion of propellant and withstands the high pressure generated by the combustion of propellant. The shape accuracy of the combustion chamber shell directly affects the accuracy of the rocket engine charge and the precise control of the flight trajectory. The strength, elongation and other mechanical properties of the combustor shell directly affect the pressure bearing capacity of the combustor shel...

Claims

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Application Information

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IPC IPC(8): B23P15/00
CPCB23P15/00F02K9/34
Inventor 和玉晓杨江波卢启辉唐伟廖东
Owner 湖北三江航天江北机械工程有限公司
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