CN106493502A - A kind of restorative procedure of aero-engine bridle end wear - Google Patents
A kind of restorative procedure of aero-engine bridle end wear Download PDFInfo
- Publication number
- CN106493502A CN106493502A CN201611006727.6A CN201611006727A CN106493502A CN 106493502 A CN106493502 A CN 106493502A CN 201611006727 A CN201611006727 A CN 201611006727A CN 106493502 A CN106493502 A CN 106493502A
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- Prior art keywords
- welding
- coating
- aero
- engine
- bridle
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The present invention relates to a kind of restorative procedure of aero-engine bridle end wear, comprises the following steps：S1, built-up welding：Using argon arc welding in abrasion 1.8～2.0 mm of surface build-up welding, gage of wire is 1.2～2.5 mm, and welding current is 25～30 A；S2, polishing：Manual grinding overlay cladding, makes size meet use requirement；S3, electric spark coating：One layer of CoCrW alloy is coated to built-up welding end face using the method that electric spark is coated, the coating layer thickness of coating is 0.04～0.05mm, and coating voltage is 40～50V, and coating frequency is 500Hz, and coating power is 800～1000W.It is an advantage of the current invention that：Argon arc-welding built-up welding is carried out using HGH625 first, form GH625 high temperature alloy layers, its feature is that hardness is relatively low, shape required for easily polishing is processed into, then one layer of CoCrW alloy is coated with, improve can end face wearability, the features such as therefore this compound repair method has low cost, efficiency high, good face size handling ease wearability, can be widely applied to the reparation of aero-engine bridle end wear.
Description
Technical field
The present invention relates to aerial motor spare part maintenance field, particularly a kind of aero-engine bridle end wear
Restorative procedure.
Background technology
Bridle end wear is found when certain type aero-engine decomposes overhaul and causes to scrap.The material of bridle is casting
High temperature alloy K424 is made, end wear amount is 1.0～1.5 mm.In order to repair the end face, conventional method is to spray or weld
One layer of wearing layer is to abrasion end face.If adopting spraying method, adhesion is poor, is easily caused coating and takes off during skimming wear
Fall.If adopting argon arc welding, the end face can be caused not wear-resisting and Fast Wearing if carrying out repairing sizes from common high temperature alloy
Failure is according to whole wearable hard alloys, as thermal coefficient of expansion and matrix difference greatly and are easily cracked and wear-resisting
Alloy is difficult in the dimensioned of heap postwelding, and efficiency is low.Therefore, bridle end wear needs a kind of low cost, efficiency high, resistance to
Mill property is high, the easy restorative procedure of dimensioned.
Content of the invention
It is an object of the invention to overcoming the shortcoming of prior art, there is provided a kind of low cost, efficiency high, face size processing
The restorative procedure of the good aero-engine bridle end wear of easy wearability.
The purpose of the present invention is achieved through the following technical solutions：A kind of reparation of aero-engine bridle end wear
Method, comprises the following steps：
S1, built-up welding：Using argon arc welding abrasion 1.8～2.0 mm of surface build-up welding, gage of wire be 1.2～2.5 mm, welding current
For 25～30 A；
S2, polishing：Manual grinding overlay cladding, makes size meet use requirement；
S3, electric spark coating：One layer of CoCrW alloy is coated to built-up welding end face, the coating of coating using the method that electric spark is coated
Thickness is 0.04～0.05mm, and coating voltage is 40～50V, and coating frequency is 500Hz, and coating power is 800～1000W.
The welding wire is HGH625 welding wires.
In step S2, the instrument of manual grinding adopts pneumatic polishing pen.
The chemical composition of the CoCrW alloys is：Chromium is 28～32wt%, and tungsten is 3.5～5.5wt%, and nickel is 3wt%, and ferrum is
3wt%, carbon are 0.9～1.4wt%, and manganese is 2wt%, and molybdenum is 1.5wt%, and cobalt is surplus.
The present invention has advantages below：
The present invention first carries out argon arc-welding built-up welding using HGH625, forms GH625 high temperature alloy layers, its feature be hardness relatively
Low, required for easily polishing is processed into shape, is then coated with one layer of CoCrW alloy, improves can end face wearability, because
The features such as this this compound repair method has low cost, efficiency high, good face size handling ease wearability, the method reparation
Bridle meet an overhaul life requirement, can be widely applied to the reparation of aero-engine bridle end wear.
Specific embodiment
With reference to embodiment, the present invention will be further described, but protection scope of the present invention is not limited to following institute
State.
【Embodiment 1】
1.3 mm of certain type aero-engine bridle end wear and scrap, using the present invention provide method repaired：Bag
Include following steps：
S1, built-up welding：Using argon arc welding in abrasion 1.8 mm of surface build-up welding, welding wire is HGH625 welding wires, and gage of wire is 1.2mm, weldering
Electric current is connect for 30A；
S2, polishing：Using pneumatic polishing manual grinding overlay cladding, size is made to meet use requirement；
S3, electric spark coating：One layer of CoCrW alloy is coated to built-up welding end face using the method that electric spark is coated, alloy into
It is divided into：Chromium is 28wt%, and tungsten is 3.5wt%, and nickel is 3wt%, and ferrum is 3wt%, and carbon is 1.4wt%, and manganese is 2wt%, and molybdenum is 1.5wt%, cobalt
For surplus, the coating layer thickness of coating is 0.04mm, and coating voltage is 40V, and coating frequency is 500Hz, and coating power is 800W.
The requirement that one overhaul life is met using the bridle that the method is repaired.
【Embodiment 2】
1.4 mm of certain type aero-engine bridle end wear and scrap, using the present invention provide method repaired：Bag
Include following steps：
S1, built-up welding：Using argon arc welding in abrasion 1.9 mm of surface build-up welding, welding wire is HGH625 welding wires, and gage of wire is 2.0 mm, welds
Electric current is connect for 28A；
S2, polishing：Using pneumatic polishing manual grinding overlay cladding, size is made to meet use requirement；
S3, electric spark coating：One layer of CoCrW alloy is coated to built-up welding end face using the method that electric spark is coated, alloy into
It is divided into：Chromium is 30wt%, and tungsten is 4.0wt%, and nickel is 3wt%, and ferrum is 3wt%, and carbon is 1.0wt%, and manganese is 2wt%, and molybdenum is 1.5wt%, cobalt
For surplus, the coating layer thickness of coating is 0.045mm, and coating voltage is 45V, and coating frequency is 500Hz, and coating power is 900W.
The requirement that one overhaul life is met using the bridle that the method is repaired.
【Embodiment 3】
1.5 mm of certain type aero-engine bridle end wear and scrap, using the present invention provide method repaired：Bag
Include following steps：
S1, built-up welding：Using argon arc welding in abrasion 2.0 mm of surface build-up welding, welding wire is HGH625 welding wires, and gage of wire is 2.5 mm, welds
Electric current is connect for 25A；
S2, polishing：Using pneumatic polishing manual grinding overlay cladding, size is made to meet use requirement；
S3, electric spark coating：One layer of CoCrW alloy is coated to built-up welding end face using the method that electric spark is coated, alloy into
It is divided into：Chromium is 32wt%, and tungsten is 5.5wt%, and nickel is 3wt%, and ferrum is 3wt%, and carbon is 0.9 wt%, and manganese is 2wt%, and molybdenum is 1.5wt%,
Cobalt is surplus, and the coating layer thickness of coating is 0.05mm, and coating voltage is 50V, and coating frequency is 500Hz, coats power and is
1000W.
The requirement that one overhaul life is met using the bridle that the method is repaired.
Claims (4)
1. a kind of restorative procedure of aero-engine bridle end wear, it is characterised in that：Comprise the following steps：
S1, built-up welding：Using argon arc welding abrasion 1.8～2.0 mm of surface build-up welding, gage of wire be 1.2～2.5 mm, welding current
For 25～30 A；
S2, polishing：Manual grinding overlay cladding, makes size meet use requirement；
S3, electric spark coating：One layer of CoCrW alloy is coated to built-up welding end face, the coating of coating using the method that electric spark is coated
Thickness is 0.04～0.05mm, and coating voltage is 40～50V, and coating frequency is 500Hz, and coating power is 800～1000W.
2. a kind of restorative procedure of aero-engine bridle end wear according to claim 1, it is characterised in that：Described
Welding wire is HGH625 welding wires.
3. a kind of restorative procedure of aero-engine bridle end wear according to claim 1, it is characterised in that：Step
In S2, the instrument of manual grinding adopts pneumatic polishing pen.
4. a kind of restorative procedure of aero-engine bridle end wear according to claim 1, it is characterised in that：Described
The chemical composition of CoCrW alloys is：Chromium is 28～32wt%, and tungsten is 3.5～5.5wt%, and nickel is 3wt%, and ferrum is 3wt%, and carbon is 0.9
～1.4wt%, manganese are 2wt%, and molybdenum is 1.5wt%, and cobalt is surplus.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611006727.6A CN106493502A (en) | 2016-11-16 | 2016-11-16 | A kind of restorative procedure of aero-engine bridle end wear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611006727.6A CN106493502A (en) | 2016-11-16 | 2016-11-16 | A kind of restorative procedure of aero-engine bridle end wear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106493502A true CN106493502A (en) | 2017-03-15 |
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ID=58324661
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611006727.6A Pending CN106493502A (en) | 2016-11-16 | 2016-11-16 | A kind of restorative procedure of aero-engine bridle end wear |
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| CN (1) | CN106493502A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109483174A (en) * | 2018-12-18 | 2019-03-19 | 重庆跃进机械厂有限公司 | A kind of processing method of diesel valve seat |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1417360A (en) * | 2001-11-07 | 2003-05-14 | 中国科学院金属研究所 | Anticorrosive and antiwear cast cobalt-base alloy |
| JP2005232575A (en) * | 2004-02-23 | 2005-09-02 | Mitsubishi Heavy Ind Ltd | Precipitation hardening type martensitic steel, and turbine blade using the same |
| CN103511000A (en) * | 2012-06-20 | 2014-01-15 | 通用电气公司 | Erosion and corrosion resistant coatings for exhaust gas recirculation based gas turbines |
| CN104372205A (en) * | 2014-10-29 | 2015-02-25 | 沈阳黎明航空发动机(集团)有限责任公司 | CoCrW-base high-temperature alloy powder for engine turbine shroud ring wear-resistant coatings and preparation method thereof |
| CN105149861A (en) * | 2015-10-19 | 2015-12-16 | 东方电气集团东方汽轮机有限公司 | Method for repairing damaged precision part of turbine |
| CN105598655A (en) * | 2016-03-02 | 2016-05-25 | 华北水利水电大学 | Method for strengthening surface of metal turbine runner blade through combination of electric spark deposition and welding |
| CN106002080A (en) * | 2016-06-23 | 2016-10-12 | 中国人民解放军第五七九工厂 | Method for repairing abraded end face of arrester |
-
2016
- 2016-11-16 CN CN201611006727.6A patent/CN106493502A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1417360A (en) * | 2001-11-07 | 2003-05-14 | 中国科学院金属研究所 | Anticorrosive and antiwear cast cobalt-base alloy |
| JP2005232575A (en) * | 2004-02-23 | 2005-09-02 | Mitsubishi Heavy Ind Ltd | Precipitation hardening type martensitic steel, and turbine blade using the same |
| CN103511000A (en) * | 2012-06-20 | 2014-01-15 | 通用电气公司 | Erosion and corrosion resistant coatings for exhaust gas recirculation based gas turbines |
| CN104372205A (en) * | 2014-10-29 | 2015-02-25 | 沈阳黎明航空发动机(集团)有限责任公司 | CoCrW-base high-temperature alloy powder for engine turbine shroud ring wear-resistant coatings and preparation method thereof |
| CN105149861A (en) * | 2015-10-19 | 2015-12-16 | 东方电气集团东方汽轮机有限公司 | Method for repairing damaged precision part of turbine |
| CN105598655A (en) * | 2016-03-02 | 2016-05-25 | 华北水利水电大学 | Method for strengthening surface of metal turbine runner blade through combination of electric spark deposition and welding |
| CN106002080A (en) * | 2016-06-23 | 2016-10-12 | 中国人民解放军第五七九工厂 | Method for repairing abraded end face of arrester |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109483174A (en) * | 2018-12-18 | 2019-03-19 | 重庆跃进机械厂有限公司 | A kind of processing method of diesel valve seat |
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Application publication date: 20170315 |