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Manufacturing method of hollow blade of turbine rotor

A technology for hollow blades and a manufacturing method, which is applied in the field of manufacturing hollow blades of turbine rotors, can solve the problems of adverse effects on the overall performance of aero-engines, reduced service life of turbine rotors, unstable castings in size and quality, and shortens the production cycle. The effect of saving costs and reducing the preparation time

Inactive Publication Date: 2018-08-07
广汉天空动力机械有限责任公司
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Problems solved by technology

[0008] The purpose of the present invention is to solve the problem that the existing turbine rotor hollow blades produced by precision casting and finishing process not only have high production cost, long cycle time and high scrap rate, but also metallurgical defects are difficult to avoid, the casting size and quality are unstable, and the finished product Low efficiency, thus reducing the service life of the turbine rotor and adversely affecting the overall performance of the aero-engine

Method used

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  • Manufacturing method of hollow blade of turbine rotor
  • Manufacturing method of hollow blade of turbine rotor
  • Manufacturing method of hollow blade of turbine rotor

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Embodiment 1

[0039] as attached figure 1 , attached figure 2 , attached image 3The manufacturing method of a turbine rotor hollow blade shown in this embodiment includes a turbine rotor hollow blade 1, an upper blade 2, a lower blade 3, a positioning pin hole 4, a gas film hole 5, an internal cavity 6, a dividing surface 7, and an outer surface 8. The metallurgical process of metal forgings is mature and the operation method is simple. Therefore, the turbine rotor hollow blade 1 uses forgings as raw materials. Compared with the precision casting turbine rotor hollow blade 1, the crystal processing does not require special casting equipment and high-precision casting molds and cores. And the pouring system, which greatly reduces the preparation time in the early stage, saves costs, and shortens the production cycle of the blade; the metal performance of the forged piece is good, so the blade formed by the machined blade is more stable than the blade formed by casting, and the looseness i...

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Abstract

The invention relates to the field of aero-engines and gas turbines, in particular to a machining technique of a hollow blade of a turbine rotor in an aero-engine combustor. A forge piece is adopted as a raw material for the blade, and the machining technique of the blade includes the following steps: (1) cutting; (2) milling or electrical discharge machining; (3) trial assembly; (4) prearrangement of solder; (5) vacuum brazing; (6) finish milling; (7) punching; (8) polishing. The machining technique is easy to operate, and solves the following problems of a conventional hollow blade for the turbine rotor, produced by adopting a method of finish machining after precision casting: the production cost is high, the period is long, the rejection rate is high, moreover, metallurgical defects can hardly be avoided, the size and quality of castings are not stable, the finished product rate is low, as a result, the service life of the turbine rotor is shortened, the overall performance of an aero-engine is adversely affected, and the like.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a method for manufacturing hollow blades of turbine rotors of aero-engines. Background technique [0002] Aeroengine turbine rotor hollow blades are very critical parts in aeroengines. There are complex cold runner inner cavities densely distributed inside and streamlined surfaces on the outside. The whole part structure is very complicated, so the material and The processing technology is extremely demanding, and the conventional process method is difficult to manufacture. The process of finishing after integral precision casting is generally used, but the overall precision casting has the following problems: [0003] 1: Aeroengine turbine blades manufactured by special precision casting methods must be made of high-precision ceramic cores. Generally, each blade must undergo multiple process tests to determine the process parameters such as core structure, casting shrinkage...

Claims

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Application Information

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IPC IPC(8): B23P15/00B23P15/04
CPCB23P15/00B23P15/04
Inventor 张云杰吴超杰韩勇黄林娄涛凌贵方
Owner 广汉天空动力机械有限责任公司
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