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Method for manufacturing box shell of large special-shaped low-pressure turbine used for aircraft engine

A low-pressure turbine, aero-engine technology, applied in engine components, mechanical equipment, etc., can solve problems such as the stability defect of the gate housing, the low utilization rate of production materials, and the incomplete flow line of forgings, so as to ensure consistency and stability. The effect of high stability, short manufacturing cycle and complete metal streamline

Inactive Publication Date: 2014-01-22
GUIZHOU AVIATION TECHN DEV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a method for manufacturing a large-scale special-shaped low-pressure turbine casing for an aero-engine, which solves the stability defects in the production of the brake casing in the prior art, the incomplete flow line of the forging, the low utilization rate of production materials, and the manufacturing high cost

Method used

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  • Method for manufacturing box shell of large special-shaped low-pressure turbine used for aircraft engine
  • Method for manufacturing box shell of large special-shaped low-pressure turbine used for aircraft engine
  • Method for manufacturing box shell of large special-shaped low-pressure turbine used for aircraft engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0034] (1) Cutting and heating:

[0035] The GH4169 alloy billet is chamfered to R20mm, and the billet is heated by three-stage heating at a heating temperature of 845°C, 975°C, and 1015°C, and the holding time of each heating stage is calculated according to 6min / 10mm;

[0036] (2) Upsetting, punching, and expanding holes:

[0037] Upsetting the blank in the axial direction until the length is 44% of the original length, punching with a punch, expanding the hole until the hole diameter at one end is 72% of the hole diameter at the other end;

[0038] (3) Horse frame reaming:

[0039] Carry out reaming so that the inner diameter of the large hole is 80% of the outer diameter, the inner diameter of the small hole is 75% of the outer diameter, and the inner diameter of the small hole is 55% of the inner diameter of the large hole;

[0040] (4) Forging forming:

[0041] The forming size of the forging is that the radius of the large hole is 90% of the outer radius of the large...

Embodiment 2

[0043] (1) Cutting and heating:

[0044] The GH4169 alloy blank is chamfered to R20mm, and the blank is heated by three-stage heating at a heating temperature of 855°C, 985°C, and 1025°C, and the holding time of each heating section is calculated as 6min / 10mm;

[0045] (2) Upsetting, punching, and expanding holes:

[0046] Upsetting the blank in the axial direction until the length is 46% of the original length, punching with a punch, expanding the hole until the hole diameter at one end is 74% of the hole diameter at the other end;

[0047] (3) Horse frame reaming:

[0048] Carry out horse frame reaming so that the inner diameter of the large hole is 85% of the outer diameter, the inner diameter of the small hole is 80% of the outer diameter, and the inner diameter of the small hole is 60% of the inner diameter of the large hole;

[0049] (4) Forging forming:

[0050] The forming size of the forging is that the radius of the large hole is 95% of the outer radius of the lar...

Embodiment 3

[0052] (1) Cutting and heating:

[0053] The GH4169 alloy billet is chamfered to R20mm, and the billet is heated in a three-stage heating method with a heating temperature of 850°C, 980°C, and 1020°C, and the holding time of each heating section is calculated according to 6min / 10mm;

[0054] (2) Upsetting, punching, and expanding holes:

[0055] Upsetting the blank in the axial direction until the length is 45% of the original length, punching with a punch, expanding the hole until the diameter of one end hole is 73% of the other end hole diameter;

[0056] (3) Horse frame reaming:

[0057]Carry out saddle reaming so that the inner diameter of the large hole is 82.5% of the outer diameter, the inner diameter of the small hole is 77.5% of the outer diameter, and the inner diameter of the small hole is 57.5% of the inner diameter of the large hole;

[0058] (4) Forging forming:

[0059] The forming size of the forging is that the radius of the large hole is 92.5% of the outer...

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Abstract

The invention discloses a method for manufacturing a box shell of a large special-shaped low-pressure turbine used for an aircraft engine. A GH 4169 alloy blank is chamfered by R20mm and is heated in a three-section heating mode at the temperature of 845-855 DEG C, 975-985 DEG C and 1015-1025 DEG C, the heat-preservation time of each heating temperature section is 6min / 10mm, then upsetting, punching, hole expanding and trestle chambering are carried out, and ultimately the box shell is finished through forged forming. According to the method, a large special-shaped bearing ring supercritical rolling technique replaces a traditional rectangular ring rolling technique, part metal flow lines are complete, large amounts of mechanical machining is needless, performance is excellent, the use rate of materials is high, raw materials are saved, manufacturing cost is low, the manufacturing cycle is short, structural stress inside a product is basically eliminated, and follow-up machining performance of the product is guaranteed.

Description

technical field [0001] The invention relates to a method for manufacturing a large-scale special-shaped low-pressure turbine casing for an aero-engine. Background technique [0002] GH4169 alloy is a nickel-based superalloy, which has good comprehensive properties in the temperature range of -253 to 700°C, and its yield strength below 650°C ranks first among deformed superalloys, and has good fatigue resistance, radiation resistance, oxidation resistance, and corrosion resistance. Corrosion performance, as well as good processing performance, welding performance and long-term organizational stability, can manufacture various parts with complex shapes, and has been widely used in the above temperature range in aerospace, nuclear energy, and petroleum industries. In the past, the production of large casings was completed by machining multiple rectangular ring forgings and then welding. The disadvantages are: on the one hand, the requirements for machining precision are relativ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B21K3/00B21J1/00B21J1/06
Inventor 杨家典罗鸿飞张建军张军博卢永恒
Owner GUIZHOU AVIATION TECHN DEV
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