KR101375636B1 - Method of tungsten carbide coating for bushing and tungsten carbide coated bushing - Google Patents

Method of tungsten carbide coating for bushing and tungsten carbide coated bushing Download PDF

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KR101375636B1
KR101375636B1 KR1020120148179A KR20120148179A KR101375636B1 KR 101375636 B1 KR101375636 B1 KR 101375636B1 KR 1020120148179 A KR1020120148179 A KR 1020120148179A KR 20120148179 A KR20120148179 A KR 20120148179A KR 101375636 B1 KR101375636 B1 KR 101375636B1
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South Korea
Prior art keywords
bushing
masking
tungsten carbide
coating
coated
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KR1020120148179A
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Korean (ko)
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양순철
신동걸
노정현
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주식회사 윈트
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/06—Sliding surface mainly made of metal
    • F16C33/12—Structural composition; Use of special materials or surface treatments, e.g. for rust-proofing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/226—Carbides
    • F05D2300/2263—Carbides of tungsten, e.g. WC
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The present invention relates to a method for manufacturing a tungsten carbide coated bushing and, more specifically, to a method for manufacturing a tungsten carbide coated bushing capable of increasing productivity by enhancing a process for manufacturing an expensive aviation part (Bushing) requiring high precision and durability. The present invention provides a method for manufacturing a tungsten carbide coated bushing and a tungsten carbide coated bushing manufactured by the method. The method for manufacturing a tungsten carbide coated bushing is to form a tungsten carbide coated layer on a coated part formed on the inner surface of the bushing except a non-coated part. The method comprises: a ring coupling step of inserting a masking ring in the non-coated part of the bushing; a bushing setting step of fixing the bushing by assembling a masking cap after putting an internal groove of a masking body, and exposing the coated part through a central spraying hole of the masking cap; a coating step of forming a primary coating layer only on the coated part by allowing a coating nozzle entered in the spraying hole to spray coating materials; a disassembling step of separating the masking ring after the coated bushing is drawn out from the masking body; and a polishing step of polishing a secondary coating layer after putting the bushing in a polishing device. [Reference numerals] (S1) Machine a bushing lathe; (S2) Assemble a masking ring; (S3) Assemble a masking body and a cap; (S4) Coat a tungsten carbide; (S5) Separate a masking body and the cap; (S6) Cut a coating layer; (S7) End

Description

텅스텐 카바이드 코팅 부싱의 제조방법 및 이에 의해 제조된 텅스텐 카바이드 코팅 부싱{Method of tungsten carbide coating for bushing and tungsten carbide coated bushing}Method of manufacturing tungsten carbide coated bushing and tungsten carbide coated bushing produced thereby

본 발명은 텅스텐 카바이드 코팅 부싱의 제조방법에 관한 것으로, 보다 상세하게는 고가이면서 고도의 정밀도 및 내구성을 요구하는 항공부품(부싱)의 제조공정을 개선하여 생산성을 향상시키게 되는 텅스텐 카바이드 코팅 부싱의 제조방법 및 이에 의해 제조된 텅스텐 카바이드 코팅 부싱에 관한 것이다.The present invention relates to a method of manufacturing a tungsten carbide coated bush, and more particularly, to manufacturing a tungsten carbide coated bush to improve productivity by improving a manufacturing process of an aeronautical component (bushing) which requires high precision and high precision and durability. A method and a tungsten carbide coated bushing produced thereby.

일반적으로, 항공기 터빈엔진의 HPC FWD CASE는 엔진의 중간부에 위치하여 고압 압축공기를 생성하는 콤프레서의 공기 흐름 통로역할을 수행하며, 고정익(Stator vane)들을 지지하는 역할을 병행한다. 여기서, 상기 HPC FWD CASE와 가변익(Variable stator vane) 사이에는 금속성 부싱(Bushing)을 구비함에 따라, 상기 가변익의 회전동작을 안내하면서 고도의 내마모성 및 내구성을 제공하게 된다.In general, the HPC FWD CASE of an aircraft turbine engine is located in the middle of the engine, serves as an air flow passage of the compressor to generate high pressure compressed air, and serves to support the stator vanes. Here, a metal bushing is provided between the HPC FWD CASE and the variable stator vane, thereby providing high wear resistance and durability while guiding the rotation of the variable blade.

이를 위해, 상기의 부싱(1)은 회전접촉이 빈번하게 발생하는 내면의 회전 접촉면에 코팅재(C)를 코팅하여 내마모성 및 강도를 증대시키게 된다.To this end, the bushing 1 is to coat the coating material (C) on the rotary contact surface of the inner surface in which the rotary contact occurs frequently to increase the wear resistance and strength.

여기서, 도 1 및 도 2를 참조하여 종래의 선행기술에 따른 부싱의 내면 코팅방법을 개략적으로 살펴보면, 상기 부싱(1)은 내면에 코팅노즐(100)로 코팅재(C)를 분사하여 소정의 두께로 1차 코팅층(C1)을 형성시킨다. 이렇게 코팅된 제1코팅층은 표면이 불균일하기 때문에 소정의 절삭수단에 의해 절삭가공하여 2차 코팅층(C2)으로 가공하게 된다. Here, referring to Figures 1 and 2 schematically illustrating a method of coating the inner surface of the bushing according to the prior art, the bushing (1) is a predetermined thickness by spraying the coating material (C) with a coating nozzle 100 on the inner surface To form a primary coating layer (C1). Since the coated first coating layer has a non-uniform surface, the first coating layer is cut by a predetermined cutting means and processed into the secondary coating layer C2.

이때, 상기의 부싱(1)은 조립공정에서 내면의 코팅부(2)에만 코팅층을 요구하고 있어서, 도 2b에서처럼 비코팅부(3)의 코팅층을 제거하는 별도의 가공공정이 필요할 뿐만 아니라 경질의 코팅층을 제거하는 공정이 매우 난해하며, 생산성 저하를 가져오고 제품의 품질, 정밀도가 현저히 저하되며 불량의 발생률이 높고 비효율적인 문제점이 있었다.At this time, the bushing (1) requires only a coating layer on the inner coating portion (2) in the assembling process, as shown in Figure 2b not only requires a separate processing step for removing the coating layer of the uncoated portion (3) The process of removing the coating layer is very difficult, bringing about a decrease in the productivity, the quality, precision of the product is significantly reduced, high incidence of defects and inefficient problems.

1.국내특허출원 제10-2004-0100790호(2004.12.03.)1.Domestic Patent Application No. 10-2004-0100790 (2004.12.03.)

본 발명의 목적은 부싱의 내면 비코팅부에 마스킹링을 끼워 나머지의 코팅부에만 코팅재가 코팅층이 형성되게 하며, 상기의 마스킹링을 분리한 후 코팅층을 정밀하게 절삭가공할 수 있게 됨에 따라, 상기 부싱의 생산성, 정밀도, 품질 등을 한층더 향상시킬 수 있게 되는 텅스텐 카바이드 코팅 부싱의 제조방법을 제공하는 데 있다.An object of the present invention is to insert a masking ring on the inner uncoated portion of the bushing so that the coating material is formed only on the remaining coating part, and after the masking ring is separated, the coating layer can be precisely cut and processed. The present invention provides a method of manufacturing a tungsten carbide coated bush that can further improve the productivity, precision and quality of the bushing.

본 발명은, 부싱 내면의 비코팅부를 제외한 나머지 코팅부에 텅스텐 카바이드 코팅층을 형성하게 되는 텅스텐 카바이드 코팅 부싱의 제조방법에 있어서, 상기 부싱의 내측 비코팅부에 마스킹링을 삽입하는 링 결합단계와; 상기 부싱을 마스킹바디의 내측 홈부에 투입하고 마스킹캡을 조립하여 부싱을 고정되며, 상기 마스킹캡의 중앙 분사구멍을 통해 코팅부가 노출되어 있는 부싱 셋팅단계와; 상기 분사구멍으로 코팅노즐을 진입시키고 코팅재를 분사하여 상기의 코팅부에만 1차 코팅층을 형성시키는 코팅단계와; 상기와 같이 코팅된 부싱을 마스킹바디에서 인출한 후 상기 마스킹링을 분리하는 분해단계와; 상기의 부싱을 연마장치에 투입하고 2차 코팅층을 연마가공하는 정삭단계로 이루어지게 되되, 상기의 부싱 셋팅단계는, 상기 홈부의 내측에 형성되어 있는 제2홈부에 마스킹링의 하단 돌출테가 걸쳐진 채, 상기 코팅노즐을 통해 고압으로 분사되는 코팅재의 분사압력에 의해 마스킹링이 임의대로 분리되지 않게 되는 것을 특징으로 하는 텅스텐 카바이드 코팅 부싱의 제조방법 및, 이에 의해 제조된 것을 특징으로 하는 텅스텐 카바이드 코팅 부싱을 제안한다.The present invention provides a tungsten carbide coated bushing method for forming a tungsten carbide coating layer on the remaining coating portion except for an uncoated portion of an inner surface of the bushing, the ring coupling step of inserting a masking ring into an inner uncoated portion of the bushing; A bushing setting step of inserting the bushing into an inner groove of a masking body and assembling a masking cap to fix the bushing and exposing a coating part through a central spray hole of the masking cap; A coating step of entering a coating nozzle into the spray hole and spraying a coating material to form a primary coating layer only on the coating part; A disassembling step of separating the masking ring after withdrawing the coated bushing from the masking body as described above; The bushing is introduced into the polishing apparatus and the finishing step of polishing the secondary coating layer is performed. The bushing setting step includes a bottom protruding frame of the masking ring that is formed in the second groove formed inside the groove. And tungsten carbide coating bushing, characterized in that the masking ring is not separated by the injection pressure of the coating material sprayed at a high pressure through the coating nozzle, and tungsten carbide coating, characterized in that Suggest a bushing.

본 발명은 마찰접촉이 빈번한 부싱의 내면에 텅스텐 카바이드 코팅층을 형성하여 내마모성 및 강도를 증대시킴은 물론, 제조공정이 간소화됨은 물론 생산성이 더욱 향상되며, 불량의 발생률을 줄이고 제품의 품질을 월등히 향상시키고 균일화하는 효과를 제공한다. 그리고 고가의 항공산업 부품의 국산화로 가격을 낮추는 경제적인 측면이 있고 부품수급을 안정화하며, 나아가 항공산업발전 및 대외적인 경쟁력을 확보할 수 있게 된다.
The present invention forms a tungsten carbide coating layer on the inner surface of the bushing with frequent frictional contact to increase abrasion resistance and strength, as well as simplify the manufacturing process and further improve productivity, reduce the incidence of defects, and greatly improve the quality of products. Provides the effect of equalization. In addition, there is an economic aspect to lower the price due to the localization of expensive aviation parts, stabilize the supply and demand of parts, and further secure aviation industry development and external competitiveness.

도 1은 일반적인 항공기 터빈엔진의 HPC FWD CASE 및 가변익(Variable stator vane)에 조립되는 부싱(1)을 예시한 도면.
도 2는 종래의 선행기술에 따른 부싱(1)의 내면에 코팅재(C)를 분사하는 과정을 나타낸 도면.
도 2a는 상기 부싱(1)의 코팅부(2)와 비코팅부(3) 모두에 코팅층이 형성된 상태의 도면.
도 2b는 상기 부싱의 비코팅부에 코팅된 코팅층(C1)을 제거하는 상태의 도면.
도 2c는 상기 코팅부의 코팅층(C1)을 절삭가공하는 상태의 도면.
도 3은 본 발명의 바람직한 실시 예에 따른 텅스텐 카바이드 코팅 부싱의 제조방법을 간략하게 나타낸 흐름도.
도 4는 본 발명에 따른 부싱에 마스킹링 및 바스킹바디가 결합된 상태에서 코팅재를 코팅하는 도면.
도 5는 본 발명의 다른 실시 예에 따른 부싱의 형태를 예시한 도면.
도 56은 본 발명에 따른 부싱의 비코팅면에서 마스킹링을 분리한 상태의 도면.
도 7은 본 발명에 따른 부싱의 1차 코팅층을 연마가공하여 2차 코팅층 상태의 도면.
도 8은 본 발명의 다른 실시 예에 따라 상기의 부싱에 끼워진 마스킹링이 마스킹바디의 내측 걸림턱에 고정된 상태를 단면으로 나타낸 도면.
도 9는 본 발명의 또 다른 실시 예에 따른 마스킹링을 나타낸 도면.1 illustrates a bushing 1 assembled to an HPC FWD CASE and a variable stator vane of a typical aircraft turbine engine.
2 is a view showing a process of spraying the coating material (C) on the inner surface of the bushing (1) according to the prior art.
Figure 2a is a view showing a coating layer formed on both the coating portion 2 and the non-coating portion 3 of the bushing (1).
Figure 2b is a view of removing the coating layer (C1) coated on the uncoated portion of the bushing.
Figure 2c is a view of a state of cutting the coating layer (C1) of the coating portion.
3 is a flow chart briefly illustrating a method of manufacturing a tungsten carbide coated bushing according to a preferred embodiment of the present invention.
Figure 4 is a view of coating the coating material in the masking ring and the masking body is coupled to the bushing according to the present invention.
5 illustrates a shape of a bushing according to another embodiment of the present invention.
56 is a view of the masking ring separated from the uncoated surface of the bushing according to the present invention.
7 is a view of the secondary coating layer state by polishing the primary coating layer of the bushing according to the present invention.
8 is a cross-sectional view illustrating a state in which a masking ring fitted to the bushing is fixed to an inner locking jaw of a masking body according to another embodiment of the present invention.
9 is a view showing a masking ring according to another embodiment of the present invention.

이하 본 발명의 실시 예를 첨부된 도면을 참조하여 상세히 설명하기로 한다. 이에 관련된 공지기능 혹은 구성에 대한 구체적인 설명이 본 발명의 요지를 불필요하게 흐릴 수 있다고 판단되는 경우에 그 상세한 설명을 생략한다. Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. A detailed description of known functions and configurations incorporated herein will be omitted when it may make the subject matter of the present invention rather unclear.

상기 도면에 따르는 본 발명의 텅스텐 카바이드 코팅 부싱의 제조방법은, 부싱(1) 내면의 비코팅부(3)를 제외한 나머지 코팅부(2)에 텅스텐 카바이드 코팅층(C2)을 형성하게 되는 텅스텐 카바이드 코팅 부싱의 제조방법에 있어서, 상기 부싱(1)의 내측 비코팅부(3)에 마스킹링(10)을 삽입하는 링 결합단계(S2)와; 상기 부싱(1)을 마스킹바디(20)의 내측 홈부(22)에 투입하고 마스킹캡(30)을 조립하여 부싱(1)을 고정되며, 상기 마스킹캡(30)의 중앙 분사구멍(32)을 통해 코팅부(2)가 노출되어 있는 부싱 셋팅단계(S3)와; 상기 분사구멍(32)으로 코팅노즐(100)을 진입시키고 코팅재(C)를 분사하여 상기의 코팅부(2)에만 1차 코팅층(C1)을 형성시키는 코팅단계(S4)와; 상기와 같이 코팅된 부싱(1)을 마스킹바디(20)에서 인출한 후 상기 마스킹링(10)을 분리하는 분해단계(S5)와; 상기의 부싱(1)을 연마장치에 투입하고 2차 코팅층(C2)을 연마가공하는 정삭단계(S6)로 이루어지는 것을 특징으로 한다.
Tungsten carbide coating bushing method of the present invention according to the drawings, the tungsten carbide coating layer to form a tungsten carbide coating layer (C2) in the remaining coating portion (2) except for the uncoated portion (3) of the inner surface of the bushing (1) A method of manufacturing a bushing, comprising: a ring coupling step (S2) of inserting a masking ring (10) into an inner uncoated portion (3) of the bushing (1); The bushing 1 is inserted into the inner groove 22 of the masking body 20, the masking cap 30 is assembled, and the bushing 1 is fixed, and the central injection hole 32 of the masking cap 30 is fixed. A bushing setting step S3 through which the coating part 2 is exposed; A coating step (S4) of entering the coating nozzle (100) into the spray hole (32) and spraying a coating material (C) to form a primary coating layer (C1) only on the coating part (2); A disassembling step (S5) of separating the masking ring 10 after withdrawing the coated bushing 1 from the masking body 20; It is characterized in that the bushing (1) is put into the polishing apparatus and the finishing step (S6) for polishing the secondary coating layer (C2).

위를 더욱 자세하게 설명하면 다음과 같다.The above is explained in more detail as follows.

본 발명의 텅스텐 카바이드 코팅 부싱의 제조방법은 부싱(1) 내면의 코팅부(2)에 텅스텐 카바이드 코팅층(C2)을 형성하기 위한 제조방법으로, 특히 비코팅부(3)에 마스킹링(10)을 끼워 코팅부(2)에만 코팅재(C)를 도포하게 된다. 상기의 코팅재(C)는 내마모성 및 강도가 우수한 텅스텐 카바이드(Tungsten carbide)가 사용된다.The manufacturing method of the tungsten carbide coated bushing of the present invention is a manufacturing method for forming the tungsten carbide coating layer (C2) in the coating portion (2) on the inner surface of the bushing (1), in particular the masking ring (10) on the uncoated portion (3) The coating material (C) is applied to only the coating part 2 by sandwiching the coating material. As the coating material (C), tungsten carbide having excellent wear resistance and strength is used.

이에, 상기 부싱(1)은 선반 등과 같은 공작기계에서 바이트 등으로 내면을 절삭가공하여 코팅부(2)와 비코팅부(3)가 형성되며, 상기 코팅부(2)는 단턱(4)을 두고 비코팅부보다 직경이 작게 형성된다.(S1)Thus, the bushing 1 is formed by cutting the inner surface with a bite or the like in a machine tool such as a lathe to form a coating portion 2 and an uncoated portion 3, the coating portion 2 is a step (4) The diameter is smaller than that of the uncoated portion.

상기 마스킹링(10)은 비코팅부(3)에 끼워져 선단이 단턱(4)에 긴밀하게 밀착된다.(S2) 이때 상기의 단턱(4)은 경사면 또는 곡면으로 형성되어 있어서, 이에 대응하도록 상기 마스킹링의 선단이 경사면(12) 또는 곡면으로 구성된다. 한편, 상기 마스킹링은 경사면(12)에 의해 비코팅부(3)에 삽입이 원활하고 조립이 용이하다.The masking ring 10 is fitted to the uncoated portion 3 so that the tip is closely adhered to the step 4. (S2) At this time, the step 4 is formed as an inclined surface or a curved surface, so that the masking ring 10 corresponds to the masking ring 10. The tip of the masking ring is composed of an inclined surface 12 or a curved surface. On the other hand, the masking ring is inserted into the uncoated portion (3) by the inclined surface 12 is easy to assemble.

또한 상기 마스킹링(10)의 바깥지름이 코팅부(2)의 내부지름보다 0.02~0.04mm가 작은 공차에 의해 서로 정밀하게 끼움 조립이 되고, 이로써 이어지는 코팅공정에서 임의대로 분리되지 않는다.In addition, the outer diameter of the masking ring 10 is precisely fitted to each other by a tolerance of 0.02 ~ 0.04mm smaller than the inner diameter of the coating portion 2, thereby not separated arbitrarily in the subsequent coating process.

여기서 본 발명의 다른 실시 예에 따르는 도 5를 참조하면, 상기 마스킹링(10')은 둥근 지름(D)을 가압하여 타원형으로 가압 성형하고, 그 타원을 둥근 원형으로 고정한 상태에서 비코팅부(3)에 삽입하게 된다. 이에 상기 마스킹링(10')은 타원형으로 복귀되면서 복원력에 의해 타원의 폭(D2) 방향 외 측면이 비코팅부에 더욱 긴밀하게 밀착 고정되며, 코팅공정 중에 임의대로 쉽게 분리되지 않게 된다. 한편, 상기 마스킹링(10')은 도 5에서처럼, 타원의 높이(D1)가 둥근 지름(D)보다 -0.1~2.0mm가 작게 축소 성형되는 것이 바람직하며, 이때 상대적으로 타원의 폭(D2)은 둥근 지름(D)보다 0.1~2.0mm 크게 확장되면서 복원력이 작용하는 것이다. Referring to FIG. 5 according to another embodiment of the present invention, the masking ring 10 ′ is pressurized into an elliptical shape by pressing a round diameter D, and an uncoated portion (with an ellipse fixed in a round circle). 3) will be inserted. Accordingly, the masking ring 10 'is returned to an elliptical shape, and the outer surface of the ellipse in the width (D2) direction is more closely fixed to the non-coating portion by a restoring force, and is not easily separated at any time during the coating process. On the other hand, the masking ring 10 'is, as shown in Figure 5, the height (D1) of the ellipse is preferably reduced to -0.1 ~ 2.0mm smaller than the round diameter (D), wherein the width of the ellipse (D2) Is expanded 0.1 to 2.0mm larger than the round diameter (D) is to act as a resilience.

다음, 상기 부싱(1)은 마스킹바디(20)의 내측에 고정하여 코팅공정을 위해 셋팅한다.(S3) 상기 마스킹바디(20)는 중앙 구멍(23)의 상면 내측에 홈부(22)가 형성되어 있어서, 상기 부싱(1)이 홈부(22)의 저면에 안착되고 마스킹캡(30)을 결합부(26)에 조립하여 움직이지 않게 고정한다. 상기 마스킹캡(30)은 코팅재의 유출되지 않게 차단하며, 중앙에 형성된 분사구멍(32)을 통해 코팅노즐(100)이 진입할 수 있게 된다. 이후에 상기의 마스킹바디는 하부를 코팅재 도포작업을 위한 코팅장치의 턴테이블에 고정하여 셋팅된다.Next, the bushing 1 is fixed to the inner side of the masking body 20 and set for the coating process. (S3) The masking body 20 has a groove portion 22 formed inside the upper surface of the central hole 23. Thus, the bushing 1 is seated on the bottom surface of the groove portion 22, and the masking cap 30 is assembled to the coupling portion 26 to fix it so as not to move. The masking cap 30 blocks the outflow of the coating material and allows the coating nozzle 100 to enter through the injection hole 32 formed in the center thereof. After that, the masking body is set by fixing the lower part to the turntable of the coating apparatus for the coating material coating operation.

다음, 상기와 같이 부싱(1)의 셋팅이 완료되고나면 분사구멍(32)을 통해 코팅노즐(100)이 비스듬히 진입시켜서 내면의 코팅부(2)에 코팅재(C)를 분사하고 일정한 두께로 1차 코팅층(C1)을 형성시킨다.(S4)Next, after the setting of the bushing 1 is completed as described above, the coating nozzle 100 is obliquely entered through the injection hole 32 to inject the coating material C into the coating part 2 on the inner surface and to a constant thickness 1. The primary coating layer (C1) is formed. (S4)

이후, 상기의 부싱(1)은 마스킹캡을 분리 후 마스킹바디에서 인출하게 되며 마스킹링(10)을 분리시킴에 따라, 코팅부(2)에만 1차 코팅층(C1)이 남는다.(S5)Subsequently, the bushing 1 is withdrawn from the masking body after the masking cap is separated and the masking ring 10 is separated, so that the primary coating layer C1 remains only in the coating part 2 (S5).

다음, 상기의 부싱(1)은 연마장치(미도시)에 투입하고 1차 코팅층(C1)을 숫돌 등의 연마수단으로 정밀하게 정삭가공하여 2차 코팅층(C2)을 형성시킨다.(S6) 한편, 상기 2차 코팅층(C2)은 표면정도가 6.3S미만으로 정밀하게 정삭가공하는 것이 바람직하다.Next, the bushing 1 is placed in a polishing apparatus (not shown), and the primary coating layer C1 is precisely finished by grinding means such as a grindstone to form a secondary coating layer C2. , The secondary coating layer (C2) is preferably precisely finished with a surface precision of less than 6.3S.

본 발명의 다른 실시 예에 따르면, 상기의 부싱 셋팅단계(S3)는, 상기 홈부(22)의 내측에 형성되어 있는 제2홈부(24)에 마스킹링(10)의 하단 돌출테(14)가 걸쳐진 채, 상기 코팅노즐(100)을 통해 고압으로 분사되는 코팅재(C)의 분사압력에 의해 마스킹링(10)이 임의대로 분리되지 않게 되는 것을 특징으로 한다.According to another embodiment of the present invention, in the bushing setting step (S3), the lower protruding frame 14 of the masking ring 10 is formed in the second groove part 24 formed inside the groove part 22. The masking ring 10 is not separated arbitrarily by the injection pressure of the coating material C sprayed at a high pressure through the coating nozzle 100 while being spread over.

즉, 상기 도 8에서처럼, 상기 마스킹링(10)의 하단부가 홈부(22)의 안쪽 제2홈부(24)에 끼워진 채 완전히 고정이 되고 상기 부싱이 안정적으로 셋팅이 되며, 후속 단계의 코팅공정이 원활히 수행된다.That is, as shown in FIG. 8, the lower end of the masking ring 10 is completely fixed while being fitted into the inner second groove 24 of the groove 22, and the bushing is stably set. It works smoothly.

또한, 상기 마스킹링(10)의 하단부에 돌출테(14)를 형성함에 따라, 테두리가 보강되고 상기 제2홈부(24)와의 접촉면적이 확장되면서 고정력이 증대되고 안정적이며 또, 상기 비코팅부(3)에 조립이 편리하고 역으로, 돌출테(14)를 잡고 분리하기도 용이하다.
In addition, as the protruding frame 14 is formed at the lower end of the masking ring 10, the edge is reinforced and the contact area with the second groove 24 is expanded, thereby increasing the fixing force and being stable. It is easy to assemble to (3), and conversely, it is also easy to hold and remove the protruding frame 14.

1:부싱 2:코팅부 3:비코팅부 4:단턱
10:마스킹링 12:경사면 14:돌출테 20:마스킹바디
22:홈부 23:구멍 24:제2홈부 26:결합부
30:마스킹캡 32:분사구멍 100:코팅노즐 C:코팅재
C1:1차 코팅층 C2:2차 코팅층1: Bushing 2: Coating 3: Uncoated 4: Step
10: masking ring 12: slope 14: protrusion 20: masking body
22: groove 23: hole 24: second groove 26: coupling portion
30: masking cap 32: injection hole 100: coating nozzle C: coating material
C1: 1st coating layer C2: 2nd coating layer

Claims (3)

부싱(1) 내면의 비코팅부(3)를 제외한 나머지 코팅부(2)에 텅스텐 카바이드 코팅층(C2)을 형성하게 되는 텅스텐 카바이드 코팅 부싱의 제조방법에 있어서,
상기 부싱(1)의 내측 비코팅부(3)에 마스킹링(10)을 삽입하는 링 결합단계(S2)와;
상기 부싱(1)을 마스킹바디(20)의 내측 홈부(22)에 투입하고 마스킹캡(30)을 조립하여 부싱(1)을 고정되며, 상기 마스킹캡(30)의 중앙 분사구멍(32)을 통해 코팅부(2)가 노출되어 있는 부싱 셋팅단계(S3)와;
상기 분사구멍(32)으로 코팅노즐(100)을 진입시키고 코팅재(C)를 분사하여 상기의 코팅부(2)에만 1차 코팅층(C1)을 형성시키는 코팅단계(S4)와;
상기와 같이 코팅된 부싱(1)을 마스킹바디(20)에서 인출한 후 상기 마스킹링(10)을 분리하는 분해단계(S5)와;
상기의 부싱(1)을 연마장치에 투입하고 2차 코팅층(C2)을 연마가공하는 정삭단계(S6)로 이루어지게 되되,
상기의 부싱 셋팅단계(S3)는, 상기 홈부(22)의 내측에 형성되어 있는 제2홈부(24)에 마스킹링(10)의 하단 돌출테(14)가 걸쳐진 채, 상기 코팅노즐(100)을 통해 고압으로 분사되는 코팅재(C)의 분사압력에 의해 마스킹링(10)이 임의대로 분리되지 않게 되는 것을 특징으로 하는 텅스텐 카바이드 코팅 부싱의 제조방법.
In the manufacturing method of the tungsten carbide coated bushing in which the tungsten carbide coating layer (C2) is formed in the remaining coating portion (2) except for the uncoated portion (3) on the inner surface of the bushing (1),
A ring coupling step (S2) of inserting a masking ring (10) into the inner uncoated portion (3) of the bushing (1);
The bushing 1 is inserted into the inner groove 22 of the masking body 20, the masking cap 30 is assembled, and the bushing 1 is fixed, and the central injection hole 32 of the masking cap 30 is fixed. A bushing setting step S3 through which the coating part 2 is exposed;
A coating step (S4) of entering the coating nozzle (100) into the spray hole (32) and spraying a coating material (C) to form a primary coating layer (C1) only on the coating part (2);
A disassembling step (S5) of separating the masking ring 10 after withdrawing the coated bushing 1 from the masking body 20;
The bushing (1) is put into the polishing apparatus and is made of a finishing step (S6) for polishing the secondary coating layer (C2),
In the bushing setting step (S3), the coating nozzle (100) while the lower protruding frame (14) of the masking ring (10) is covered by the second groove (24) formed inside the groove (22). Method of producing a tungsten carbide coated bushing, characterized in that the masking ring 10 is not separated by the injection pressure of the coating material (C) is injected at a high pressure through.
삭제delete 청구항 제1항에 의한 텅스텐 카바이드 코팅 부싱의 제조방법으로 제조된 것을 특징으로 하는 텅스텐 카바이드 코팅 부싱.A tungsten carbide coated bushing according to claim 1, which is manufactured by the method for producing a tungsten carbide coated bushing.
KR1020120148179A 2012-12-18 2012-12-18 Method of tungsten carbide coating for bushing and tungsten carbide coated bushing KR101375636B1 (en)

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KR20180083495A (en) 2017-01-13 2018-07-23 주식회사 윈트 Method of tungsten carbide coating for bushing and tungsten carbide coated bushing

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JPH0567361U (en) * 1992-02-19 1993-09-07 株式会社ユニシアジェックス Masking device for painting
US20070128017A1 (en) * 2005-12-05 2007-06-07 General Electric Company Variable stator vane assembly and bushing thereof
KR100936395B1 (en) * 2009-04-07 2010-01-12 주식회사 한스코 Manufacturing method shell

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0567361U (en) * 1992-02-19 1993-09-07 株式会社ユニシアジェックス Masking device for painting
US20070128017A1 (en) * 2005-12-05 2007-06-07 General Electric Company Variable stator vane assembly and bushing thereof
KR100936395B1 (en) * 2009-04-07 2010-01-12 주식회사 한스코 Manufacturing method shell

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20180083495A (en) 2017-01-13 2018-07-23 주식회사 윈트 Method of tungsten carbide coating for bushing and tungsten carbide coated bushing
KR101884551B1 (en) * 2017-01-13 2018-08-29 주식회사 윈트 Method of tungsten carbide coating for bushing and tungsten carbide coated bushing

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