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Method for manufacturing blade forging of heavy type combustion engine

A manufacturing method and technology of gas turbines, applied in the direction of manufacturing tools, other manufacturing equipment/tools, furnace types, etc., can solve problems such as lack of process parameters, failure to meet performance indicators of forgings, and technical requirements for forgings

Inactive Publication Date: 2007-10-31
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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Problems solved by technology

[0002] R0110 heavy-duty gas turbine blades are made of Russian material ЭП479 steel, and the domestic corresponding material is 1Cr16Ni2MoN, which is a new material. This work has not been carried out in China, and there are no process parameters for reference, such as the influence of deformation process on the structure and performance; heat treatment The influence on the microstructure and properties; the influence of forging heating temperature and firing times on the microstructure and properties of the blade, etc.
According to the relevant Russian technical documents, the inventor of the present invention adopts the quenching and tempering process for the raw materials at 550°C to 590°C. In order to meet the performance requirements of the technical conditions, the N content is controlled at the upper limit, and for the subsequent forgings For heat treatment, the high temperature tempering system is adopted, that is, 640 ° C ~ 680 ° C, but the performance index of the forging after treatment does not meet the technical requirements of the forging

Method used

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  • Method for manufacturing blade forging of heavy type combustion engine
  • Method for manufacturing blade forging of heavy type combustion engine
  • Method for manufacturing blade forging of heavy type combustion engine

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Experimental program
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Embodiment Construction

[0018] The actual composition of the materials is C 0.16%~0.18%, Cr 15.2%~16.2%, Ni 2.2%~2.35%, Mo 1.02%~1.13%, N 0.088%~0.094%. The forging forming process is adopted, and the final forging temperature adopts Three temperatures of 1040°C, 1120°C, and 1160°C, the deformation is greater than 25%, and it is air-cooled. Four temperatures of 630°C, 650°C, 670°C, and 690°C are used for tempering temperature. It can be seen that the plasticity index of the forging is improved by 50%, and the strength index can also meet the requirements of technical conditions. The test data are shown in Table 3 below.

[0019]

[0020] It can be seen from the data in Table 3 that when the deformation temperature is between 1040°C and 1160°C, the performance index of the forging meets the requirements of the technical conditions, and the plasticity index is very rich. The heat treatment temperature of the blade can also be determined from the above test plan.

[0021] When carrying out de...

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Abstract

The forging for heavy combustion vane uses ze pi 479 steel, with technical conditions being C 0.12%-0.18%, Cr 15%-16.5%, Ni 2.0%-2.5%, Mo 0.9%-1.3%, N 0.03%-0.10%. The final forging temperature is controlled within 1040deg.C-1160deg.C, with deformation ratio bigger than 25%. It determines the deformation temperature and heat treatment system to meet the production requirement for heavy combustion steel vanes.

Description

Technical field: [0001] The invention relates to a manufacturing method of a heavy gas turbine blade forging. Background technique: [0002] R0110 heavy-duty gas turbine blades are made of Russian material ЭП479 steel, and the domestic corresponding material is 1Cr16Ni2MoN, which is a new material. This work has not been carried out in China, and there are no process parameters for reference, such as the influence of deformation process on the structure and performance; heat treatment The influence on the microstructure and performance; the influence of forging heating temperature and fire times on the microstructure and performance of the blade, etc. According to the relevant Russian technical documents, the inventor of the present invention adopts the quenching and tempering process for the raw materials at 550°C to 590°C. In order to meet the performance requirements of the technical conditions, the N content is controlled at the upper limit, and for the subsequent forgin...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B21J5/00B23P23/04C21D11/00C21D9/00C22C38/44
Inventor 郑渠英刘秋生郭殿品邰清安胡以仁宋玺玉王丹关红史丽坤
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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