A kind of processing technology method of vortex device assembly

Abstract

The invention relates to the field of aero-engines and gas turbines, in particular to a machining technology method of a swirler assembly in an aero-engine combustion chamber. The swirler assembly iscomposed of a swirler sleeve and a swirler. The swirler sleeve and the swirler each adopt a forged piece as a raw material. The machining technology method of the swirler assembly comprises the stepsof (1) turning, (2) milling or electrosparking, (3) cleaning, (4) trial assembly, (5) positioned welding, (6) brazing filler metal prearrangement, (7) vacuum brazing, (8) pincers machining and (9) finish turning. The machining technology method is simple in operation; and the problems that in the prior art, after precision casting is adopted, a swirler assembly manufactured in a precision machining manner is high in production cost and long in period, the requirements for personnel and skills are high, metallurgical defects are hard to avoid, the size and quality of a casting are instable, therate of finished products is not high, and consequently the service life of a combustion chamber is shortened, and adverse effects are generated to the overall performance of an aero-engine are solved.

Description

technical field [0001] The invention relates to the fields of aero-engines and gas turbines, in particular to a processing method for a vortex assembly in an aero-engine combustion chamber. Background technique [0002] The vortex assembly is a very important component in the combustion chamber of an aero-engine. The vortex assembly with a vane structure is widely used in the combustion chamber of an aero-engine with a high thrust-to-weight ratio. The airflow speed forms a stable fire source at the head of the flame tube to ensure the stable operation of the combustion chamber. [0003] The vortex components are small in size and complex in structure. Multiple blades are evenly distributed along the circumferential direction between the ring walls. During scientific research and trial production or mass production, the process of finishing after integral precision casting is generally adopted, but the overall precision casting has the following problems: [0004] 1: Althoug...

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Problems solved by technology

[0009] The purpose of the present invention is to solve the problem that the existing vortex components produced by precision casting after finishing process not only have high production cost, long cycle time, high requirements on personnel and technology, but also metallurgical defects are difficult to avoid, and the size and quality of castings are not good. Stable, low yield, thus reducing the service life of the combustion chamber and adversely affecting the overall performance of the aero-engine, etc.

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