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Grinding method and grinding wheel for nickel-based high-temperature alloy turbine front sealing disc

A technology of nickel-based high-temperature alloy and grinding wheel, which is applied in grinding/polishing equipment, machine tools designed for grinding the rotating surface of workpieces, grinding machines, etc. It can solve problems such as low processing efficiency, poor quality consistency, and short tool life, and achieve The effect of improving processing efficiency, proper abrasive particle distribution density, and prolonging tool life

Active Publication Date: 2015-06-10
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] In order to overcome the shortcomings of low processing efficiency, short tool life, and poor quality consistency in the prior art, the present invention proposes a grinding method and a grinding wheel for the front seal disc of a nickel-based superalloy turbine

Method used

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  • Grinding method and grinding wheel for nickel-based high-temperature alloy turbine front sealing disc

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0024] The present embodiment is a grinding method and a grinding wheel of a nickel-base superalloy turbine front seal plate.

[0025] In this embodiment, by adopting a single-layer brazed CBN grinding wheel and using matching grinding process parameters, the high-efficiency and precise machining of this type of parts is realized, and the tasks that previously required two steps of rough machining and finishing are combined. to complete in one step. The specific process includes the following steps:

[0026] Step 1, cleaning the surface of the workpiece; using aviation cleaning gasoline to clean the semi-finished product of the front seal plate of the nickel-based superalloy turbine;

[0027] Step 2, clamping; use a clamp to clamp the nickel-based superalloy turbine front seal disc on the grinder workbench, and perform a clamping position accuracy test to ensure that the position accuracy is ±0.01mm;

[0028] Step 3, grinding; using a single-layer brazed grinding wheel, the se...

Embodiment 2

[0034] The present embodiment is a grinding method and a grinding wheel of a nickel-base superalloy turbine front seal disc.

[0035] In this embodiment, by adopting a single-layer brazed CBN grinding wheel and using matching grinding process parameters, the high-efficiency and precise machining of this type of parts is realized, and the tasks that previously required two steps of rough machining and finishing are combined. to complete in one step. The specific process includes the following steps:

[0036] Step 1, cleaning the surface of the workpiece; using aviation cleaning gasoline to clean the semi-finished product of the front seal plate of the nickel-based superalloy turbine;

[0037] Step 2, clamping; use a clamp to clamp the nickel-based superalloy turbine front seal disc on the grinder workbench, and perform a clamping position accuracy test to ensure that the position accuracy is ±0.01mm;

[0038] Step 3, grinding; using a single-layer brazed grinding wheel, the s...

Embodiment 3

[0044] The present embodiment is a grinding method and a grinding wheel of a nickel-base superalloy turbine front seal plate.

[0045] In this embodiment, by adopting a single-layer brazed CBN grinding wheel and using matching grinding process parameters, the high-efficiency and precise machining of this type of parts is realized, and the tasks that previously required two steps of rough machining and finishing are combined. to complete in one step. The specific process includes the following steps:

[0046] Step 1, cleaning the surface of the workpiece; using aviation cleaning gasoline to clean the semi-finished product of the front seal plate of the nickel-based superalloy turbine;

[0047] Step 2, clamping; use a clamp to clamp the nickel-based superalloy turbine front seal disc on the grinder workbench, and perform a clamping position accuracy test to ensure that the position accuracy is ±0.01mm;

[0048] Step 3, grinding; using a single-layer brazed grinding wheel, the ...

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Abstract

The invention discloses a grinding method and a grinding wheel for a nickel-based high-temperature alloy turbine front sealing disc. A bonding layer formed by melting and solidifying Ti-Zr-Cu-Ni alloy powder brazing filler metal adopted by the grinding wheel has a very good comprehensive mechanical property, so that a long working life of the monolayer brazed grinding wheel can be guaranteed. The CBN grinding particles on the surface of a grinding wheel base body are uniformly distributed; and the distribution density of the grinding particles is reasonably controlled, so that the grinding wheel is higher in sharpness, the processing efficiency is improved by 3-4 times, the service life of the grinding wheel is prolonged by 8-10 times, the residual pressure stress of the parts surface is reduced and the surface quality of the parts is improved. The test proves that the service life of the grinding wheel is prolonged by 8-10 times, namely the quantity of the processed parts is increased from 2 only to 16-20, and the surface roughness is improved by one level, namely the roughness value is increased from Ra 0.8 microns to Ra 0.4 microns.

Description

technical field [0001] The invention relates to a grinding method and a grinding wheel for a nickel-based high-temperature alloy turbine front seal disc, belonging to the technical field of difficult-to-machine materials and their high-efficiency and precise machining processes and tools. Background technique [0002] The front seal disc of the turbine is a key component of an aero-engine. Its structural features are as follows: the maximum outer circle of the disc is Φ587mm, the minimum inner diameter of the hollow part is Φ212mm, the total height is 55mm, and the minimum wall thickness is only 1.5mm, which is a typical Thin-walled disk parts. The overall surface of the roulette is composed of various inclined surfaces, conical surfaces and arcs, and the structure is complex. At the same time, in order to improve the performance of aero-engines, the front seal plate of the turbine is usually made of nickel-based superalloy GH4169, which is a typical high-strength toughness...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B24B5/36B24D3/06
Inventor 何坚丁文锋梁养民刘智武赵海艳汤丽王艳付蓉
Owner AECC AVIATION POWER CO LTD