CN114318206B - Wear-resistant coating for gas turbine crossfire tube and preparation method thereof - Google Patents
Wear-resistant coating for gas turbine crossfire tube and preparation method thereof Download PDFInfo
- Publication number
- CN114318206B CN114318206B CN202111517905.2A CN202111517905A CN114318206B CN 114318206 B CN114318206 B CN 114318206B CN 202111517905 A CN202111517905 A CN 202111517905A CN 114318206 B CN114318206 B CN 114318206B
- Authority
- CN
- China
- Prior art keywords
- chromium
- nickel
- coating
- powder
- wear
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000576 coating method Methods 0.000 title claims abstract description 64
- 239000011248 coating agent Substances 0.000 title claims abstract description 63
- VEMKTZHHVJILDY-UHFFFAOYSA-N resmethrin Chemical compound CC1(C)C(C=C(C)C)C1C(=O)OCC1=COC(CC=2C=CC=CC=2)=C1 VEMKTZHHVJILDY-UHFFFAOYSA-N 0.000 title claims abstract description 29
- 238000002360 preparation method Methods 0.000 title claims abstract description 10
- -1 nickel-chromium-aluminum Chemical group 0.000 claims abstract description 42
- 229910000990 Ni alloy Inorganic materials 0.000 claims abstract description 9
- HNYSBSMSUWPWOM-UHFFFAOYSA-N [Ni].[W].[Cr].[Co] Chemical group [Ni].[W].[Cr].[Co] HNYSBSMSUWPWOM-UHFFFAOYSA-N 0.000 claims abstract description 9
- 239000000843 powder Substances 0.000 claims description 57
- 239000007789 gas Substances 0.000 claims description 27
- 238000005507 spraying Methods 0.000 claims description 27
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 18
- 238000007750 plasma spraying Methods 0.000 claims description 16
- 239000002245 particle Substances 0.000 claims description 12
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 9
- 229910052786 argon Inorganic materials 0.000 claims description 9
- 238000001035 drying Methods 0.000 claims description 8
- 239000001257 hydrogen Substances 0.000 claims description 7
- 229910052739 hydrogen Inorganic materials 0.000 claims description 7
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 6
- 238000007873 sieving Methods 0.000 claims description 6
- 238000010285 flame spraying Methods 0.000 claims description 5
- 238000005488 sandblasting Methods 0.000 claims description 4
- 239000007921 spray Substances 0.000 claims description 4
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 3
- 239000003345 natural gas Substances 0.000 claims description 3
- 239000001301 oxygen Substances 0.000 claims description 3
- 229910052760 oxygen Inorganic materials 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 abstract description 25
- 239000000956 alloy Substances 0.000 abstract description 25
- 229910052751 metal Inorganic materials 0.000 abstract description 15
- 239000002184 metal Substances 0.000 abstract description 15
- 238000009991 scouring Methods 0.000 abstract description 7
- 238000012423 maintenance Methods 0.000 abstract description 5
- 238000002485 combustion reaction Methods 0.000 abstract description 4
- 238000007751 thermal spraying Methods 0.000 abstract description 3
- 239000010410 layer Substances 0.000 description 29
- 239000010935 stainless steel Substances 0.000 description 6
- 229910001220 stainless steel Inorganic materials 0.000 description 6
- 239000011159 matrix material Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 239000012790 adhesive layer Substances 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000003628 erosive effect Effects 0.000 description 2
- 238000011068 loading method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 238000012216 screening Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 239000011195 cermet Substances 0.000 description 1
- 239000011651 chromium Substances 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005261 decarburization Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000009972 noncorrosive effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 238000003892 spreading Methods 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
Landscapes
- Coating By Spraying Or Casting (AREA)
Abstract
The invention belongs to the technical field of thermal spraying, and particularly relates to a wear-resistant coating for a gas turbine crossfire tube and a preparation method thereof. The wear-resistant coating provided by the invention comprises a metal bonding layer and a hard alloy wear-resistant layer, wherein the hard alloy wear-resistant layer is covered on the metal bonding layer, the metal bonding layer is a nickel-chromium-aluminum coating or a nickel-cobalt-chromium-aluminum-yttrium coating, and the hard alloy wear-resistant layer is a cobalt-chromium-tungsten-nickel alloy coating, so that the wear resistance and the gas scouring resistance are realized. The wear-resistant coating provided by the invention can reduce the impact of gas scouring wear on the contact part of the crossfire tube and the flame tube, prolong the replacement and maintenance service life of the crossfire tube and ensure the stable operation of the combustion chamber.
Description
Technical Field
The invention belongs to the technical field of thermal spraying, and particularly relates to a wear-resistant coating for a gas turbine crossfire tube and a preparation method thereof.
Background
The service life of the high temperature components of a gas turbine is a major contributor to the operation and overhaul time of the gas turbine. Crossfire tubes are one of the indispensable parts in gas turbine single-tube, can-annular and crosstube combustors. The flame tube section is usually connected with a crossfire tube, plays a role of spreading flame and equalizing pressure, and the crossfire function of the crossfire tube section is related to the stabilization of the starting ignition of the gas turbine. The outer surface coating protection of the crossfire tube can enhance the erosion resistance and flame flow erosion resistance of the crossfire tube, reduce the frequency of replacement parts and maintenance and shutdown, and greatly save the maintenance cost of the gas turbine.
At present, various wear-resistant coating materials have been disclosed at home and abroad, and most of them have been commercially applied, for example, niCr-Cr 3 C 2 Co-WC. Carbide-containing cermet wear-resistant coatingThe use at medium and low temperatures has excellent wear and corrosion resistance characteristics, but the use at high temperatures produces a degree of decarburization, for example Co-WC is typically used in non-corrosive environments at temperatures not higher than 540 ℃. While certain hard alloy coatings can withstand higher temperatures and maintain higher hardness and wear resistance at high temperatures, are expected to be used on the surface of a combustion chamber crossfire tube.
Disclosure of Invention
The invention aims to provide an abrasion-resistant coating for a gas turbine crossfire tube and a preparation method thereof.
The wear-resistant coating for the gas turbine crossfire tube comprises a metal bonding layer and a hard alloy wear-resistant layer, wherein the hard alloy wear-resistant layer is covered above the metal bonding layer; the metal bonding layer is a nickel-chromium-aluminum coating or a nickel-cobalt-chromium-aluminum-yttrium coating and is used for transition between the matrix and the hard alloy wear-resistant layer and matching the thermal expansion coefficients of the matrix and the hard alloy wear-resistant layer; the hard alloy wear-resistant layer is a cobalt-chromium-tungsten-nickel alloy coating and plays roles of resisting wear and gas scouring.
A preparation method of a wear-resistant coating for a gas turbine crossfire tube comprises the following steps:
step 1: preparing nickel-chromium-aluminum powder with the particle size of 45-125 mu m; preparing cobalt-chromium-tungsten-nickel-silicon-carbon powder with the particle size of 53-150 mu m; carrying out sand blasting treatment on the surface of the part to be sprayed;
step 2: the cobalt chromium tungsten nickel silicon carbon powder is passed through a 150 mesh screen for powder sieving:
step 3: putting nickel-chromium-aluminum powder and cobalt-chromium-tungsten-nickel-silicon carbon powder passing through a screen into an oven, and drying at 100+/-10 ℃ for at least 1 hour;
step 4: spraying a nickel-chromium-aluminum coating by adopting atmospheric plasma spraying equipment, wherein the thickness of the coating is 0.1-0.15 mm; wherein, atmospheric plasma spraying equipment sets up to: the current is 575+/-25A, the argon gas is 50+/-5 NLPM, the hydrogen gas is 9+/-1 NLPM, the powder feeding rate is 40+/-5 g/min, and the spraying distance is 140+/-10 mm;
step 5: adopting atmospheric plasma spraying equipment to spray cobalt-chromium-tungsten-nickel alloy coating, wherein the spraying thickness is 0.45-0.55 mm; wherein, atmospheric plasma spraying equipment sets up to: current is 550+/-50A, argon is 45+/-5 NLPM, hydrogen is 9+/-1 NLPM, powder feeding rate is 50+/-5 g/min, and spraying distance is 120+/-10 mm;
step 6: the coating is machined to the assembled dimensions.
The preparation method of the wear-resistant coating for the crossfire tube of the gas turbine comprises the following steps:
step 1: preparing nickel cobalt chromium aluminum yttrium powder with the particle size of 5-38 mu m; preparing cobalt-chromium-tungsten-nickel-silicon-carbon powder with the particle size of 53-150 mu m; carrying out sand blasting treatment on the surface of the part to be sprayed;
step 2: the cobalt chromium tungsten nickel silicon carbon powder is passed through a 150 mesh screen for powder sieving:
step 3: putting nickel cobalt chromium aluminum yttrium powder and cobalt chromium tungsten nickel silicon carbon powder passing through a screen into an oven, and drying at 100+/-10 ℃ for at least 1 hour;
step 4: spraying a nickel-chromium-aluminum coating by using supersonic flame spraying equipment, wherein the thickness of the coating is 0.1-0.15 mm; wherein the supersonic flame spraying apparatus is configured to: 170+/-10 NLPM of natural gas, 240+/-5 NLPM of oxygen, 350+/-10 NLPM of shielding gas, 40+/-5 g/min of powder feeding rate and 240+/-10 mm of spraying distance;
step 5: adopting atmospheric plasma spraying equipment to spray cobalt-chromium-tungsten-nickel alloy coating, wherein the spraying thickness is 0.45-0.55 mm; wherein, atmospheric plasma spraying equipment sets up to: current is 550+/-50A, argon is 45+/-5 NLPM, hydrogen is 9+/-1 NLPM, powder feeding rate is 50+/-5 g/min, and spraying distance is 120+/-10 mm;
step 6: the coating is machined to the assembled dimensions.
The invention has the beneficial effects that:
the invention provides a wear-resistant coating for a gas turbine crossfire tube, which comprises a metal bonding layer and a hard alloy wear-resistant layer, wherein the hard alloy wear-resistant layer covers the metal bonding layer, the metal bonding layer adopts a nickel-chromium-aluminum coating or a nickel-cobalt-chromium-aluminum-yttrium coating, and the hard alloy wear-resistant layer adopts a cobalt-chromium-tungsten-nickel alloy coating, so that the effects of wear resistance and gas scouring resistance are achieved. The wear-resistant coating provided by the invention can reduce the impact of gas scouring wear on the contact part of the crossfire tube and the flame tube, prolong the replacement and maintenance service life of the crossfire tube and ensure the stable operation of the combustion chamber.
Drawings
FIG. 1 is a schematic diagram of a metallographic structure of a wear-resistant coating for a gas turbine crossfire tube.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
Example 1:
the invention provides a wear-resistant coating for a gas turbine crossfire tube, which consists of a metal bonding layer and a hard alloy wear-resistant layer. The metal bonding layer is a nickel-chromium-aluminum coating or a nickel-cobalt-chromium-aluminum-yttrium coating, the bonding layer can not only increase the bonding force of the wear-resistant coating, but also play a role in transition between the matrix and the hard alloy wear-resistant coating, the thermal expansion coefficients of the matrix and the hard alloy wear-resistant coating are matched, and the nickel-chromium-aluminum coating and the nickel-cobalt-chromium-aluminum-yttrium coating can bear the temperature of up to 980 ℃. The hard alloy wear-resistant layer is a cobalt-chromium-tungsten-nickel alloy coating and can play a role in resisting wear and gas scouring. As shown in fig. 1, which is a schematic diagram of the metallographic structure of the wear-resistant coating, a nickel-chromium-aluminum bonding layer 2 is positioned between a part substrate 1 and a cobalt-chromium-tungsten-nickel alloy coating 3.
Example 2:
the invention provides a process method for preparing a wear-resistant coating of a crossfire tube of a gas turbine, which is used for preparing the wear-resistant coating with reliable quality on the surface of the crossfire tube. The technical scheme of the invention is that the coating comprises a metal bonding layer and a hard alloy wear-resistant layer, wherein the metal bonding layer is nickel-chromium-aluminum powder or cobalt-nickel-chromium-aluminum-yttrium powder, and the wear-resistant coating is hard alloy powder. Before spraying the surface of the part, blowing sand to the surface of the part, preparing each coating by using a thermal spraying mode, and finally turning to the assembly size.
The metal bonding layer is selected from nickel-chromium-aluminum (brand Metco 443 NS) powder with the particle size of 45-125 mu m, the hard alloy wear-resistant layer is selected from cobalt-chromium-tungsten-nickel-silicon-carbon (brand Wallex6#) powder with the particle size of 53-150 mu m, and the powder is used after being screened through a 150-mesh sieve.
The preparation method comprises the following steps:
step 1: powder screening: sieving Wallex6# powder with a 150-mesh stainless steel screen, and loading undersize into a powder barrel with the noted name;
step 2: powder drying: placing the powder raw materials to be used in a stainless steel tray with the powder names noted, placing the stainless steel tray in an oven at 100+/-10 ℃, and drying for at least 1 hour;
step 3: and (3) spraying an adhesive layer: adopting an atmospheric plasma spraying device, wherein the current is 575+/-25A, the argon is 50+/-5 NLPM, the hydrogen is 9+/-1 NLPM, the powder feeding rate is 40+/-5 g/min, the spraying distance is 140+/-10 mm, and the thickness of a nickel-chromium-aluminum coating is 0.1-0.15 mm;
step 4: spraying a hard alloy wear-resistant layer: adopting an atmospheric plasma spraying device, wherein the current is 550+/-50A, the argon is 45+/-5 NLPM, the hydrogen is 9+/-1 NLPM, the powder feeding rate is 50+/-5 g/min, the spraying distance is 120+/-10 mm, and the spraying thickness is 0.45-0.55 mm;
step 5: and (3) using a YC09 hard alloy turning tool, wherein the cutting linear speed is 30-50 m/min, and feeding a turning coating of 0.1-0.15 mm to the assembly size.
According to the invention, the outer wall of the crossfire tube is coated with the high-temperature-resistant hard alloy type wear-resistant coating by adopting an atmospheric plasma spraying method, so that the impact of gas scouring wear on the contact part of the crossfire tube is reduced, the replacement and maintenance service life of the crossfire tube are prolonged, and the stable operation of the combustion chamber is ensured.
Example 3:
the metal bonding layer is selected from nickel cobalt chromium aluminum yttrium (trademark Amdry 997) powder with the particle size of 5-38 mu m, the hard alloy wear-resistant layer is selected from cobalt chromium tungsten nickel silicon carbon (trademark Wallex6#) powder with the particle size of 53-150 mu m, and the powder is used after being sieved by a 150-mesh sieve.
Step 1: powder screening: sieving Wallex6# powder with a 150-mesh stainless steel screen, and loading undersize into a powder barrel with the noted name;
step 2: powder drying: placing the powder raw materials to be used in a stainless steel tray with the powder names noted, placing the stainless steel tray in an oven at 100+/-10 ℃, and drying for at least 1 hour;
step 3: and (3) spraying an adhesive layer: adopting supersonic flame spraying equipment, wherein natural gas is 170+/-10 NLPM, oxygen is 240+/-5 NLPM, shielding gas is 350+/-10 NLPM, powder feeding rate is 40+/-5 g/min, spraying distance is 240+/-10 mm, and nickel-chromium-aluminum coating is sprayed with the thickness of 0.1-0.15 mm;
step 4: spraying a hard alloy wear-resistant layer: adopting an atmospheric plasma spraying device, wherein the current is 550+/-50A, the argon is 45+/-5 NLPM, the hydrogen is 9+/-1 NLPM, the powder feeding rate is 50+/-5 g/min, the spraying distance is 120+/-10 mm, and the spraying thickness is 0.45-0.55 mm;
step 5: and (3) using a YC09 hard alloy turning tool, wherein the cutting linear speed is 30-50 m/min, and feeding a turning coating of 0.1-0.15 mm to the assembly size.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. The preparation method of the wear-resistant coating for the crossfire tube of the gas turbine is characterized by comprising the following steps of:
step 1: preparing nickel-chromium-aluminum powder with the particle size of 45-125 mu m; preparing cobalt-chromium-tungsten-nickel-silicon-carbon powder with the particle size of 53-150 mu m; carrying out sand blasting treatment on the surface of the part to be sprayed;
step 2: the cobalt chromium tungsten nickel silicon carbon powder is passed through a 150 mesh screen for powder sieving:
step 3: putting nickel-chromium-aluminum powder and cobalt-chromium-tungsten-nickel-silicon carbon powder passing through a screen into an oven, and drying at 100+/-10 ℃ for at least 1 hour;
step 4: spraying a nickel-chromium-aluminum coating by adopting atmospheric plasma spraying equipment, wherein the thickness of the coating is 0.1-0.15 mm; wherein, atmospheric plasma spraying equipment sets up to: the current is 575+/-25A, the argon gas is 50+/-5 NLPM, the hydrogen gas is 9+/-1 NLPM, the powder feeding rate is 40+/-5 g/min, and the spraying distance is 140+/-10 mm;
step 5: adopting atmospheric plasma spraying equipment to spray cobalt-chromium-tungsten-nickel alloy coating, wherein the spraying thickness is 0.45-0.55 mm; wherein, atmospheric plasma spraying equipment sets up to: current is 550+/-50A, argon is 45+/-5 NLPM, hydrogen is 9+/-1 NLPM, powder feeding rate is 50+/-5 g/min, and spraying distance is 120+/-10 mm;
step 6: the coating is machined to the assembled dimensions.
2. The preparation method of the wear-resistant coating for the crossfire tube of the gas turbine is characterized by comprising the following steps of:
step 1: preparing nickel cobalt chromium aluminum yttrium powder with the particle size of 5-38 mu m; preparing cobalt-chromium-tungsten-nickel-silicon-carbon powder with the particle size of 53-150 mu m; carrying out sand blasting treatment on the surface of the part to be sprayed;
step 2: the cobalt chromium tungsten nickel silicon carbon powder is passed through a 150 mesh screen for powder sieving:
step 3: putting nickel cobalt chromium aluminum yttrium powder and cobalt chromium tungsten nickel silicon carbon powder passing through a screen into an oven, and drying at 100+/-10 ℃ for at least 1 hour;
step 4: spraying a nickel-chromium-aluminum coating by using supersonic flame spraying equipment, wherein the thickness of the coating is 0.1-0.15 mm; wherein the supersonic flame spraying apparatus is configured to: 170+/-10 NLPM of natural gas, 240+/-5 NLPM of oxygen, 350+/-10 NLPM of shielding gas, 40+/-5 g/min of powder feeding rate and 240+/-10 mm of spraying distance;
step 5: adopting atmospheric plasma spraying equipment to spray cobalt-chromium-tungsten-nickel alloy coating, wherein the spraying thickness is 0.45-0.55 mm; wherein, atmospheric plasma spraying equipment sets up to: current is 550+/-50A, argon is 45+/-5 NLPM, hydrogen is 9+/-1 NLPM, powder feeding rate is 50+/-5 g/min, and spraying distance is 120+/-10 mm;
step 6: the coating is machined to the assembled dimensions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111517905.2A CN114318206B (en) | 2021-12-13 | 2021-12-13 | Wear-resistant coating for gas turbine crossfire tube and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111517905.2A CN114318206B (en) | 2021-12-13 | 2021-12-13 | Wear-resistant coating for gas turbine crossfire tube and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114318206A CN114318206A (en) | 2022-04-12 |
| CN114318206B true CN114318206B (en) | 2023-12-05 |
Family
ID=81049892
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111517905.2A Active CN114318206B (en) | 2021-12-13 | 2021-12-13 | Wear-resistant coating for gas turbine crossfire tube and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114318206B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104087888A (en) * | 2014-06-19 | 2014-10-08 | 哈尔滨东安发动机（集团）有限公司 | Preparation method for nickel chromium-chromium carbide coating with high hardness and low porosity |
| CN106756713A (en) * | 2016-11-10 | 2017-05-31 | 哈尔滨工程大学 | Improve coating of combustion engine compressor drum barrel wearability peculiar to vessel and preparation method thereof |
| CN106929788A (en) * | 2017-05-02 | 2017-07-07 | 安徽威龙再制造科技股份有限公司 | A kind of multi-element alloy coat of sinking roller and its preparation and spraying method |
| CN109722618A (en) * | 2017-10-26 | 2019-05-07 | 沈阳黎明国际动力工业有限公司 | A kind of supersonic flame spraying technique of cobalt chromium tungsten wear-resistant coating |
| EP3904555A1 (en) * | 2018-12-29 | 2021-11-03 | Kunming University Of Science And Technology | Ultralimit alloy and preparation method therefor |
-
2021
- 2021-12-13 CN CN202111517905.2A patent/CN114318206B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104087888A (en) * | 2014-06-19 | 2014-10-08 | 哈尔滨东安发动机（集团）有限公司 | Preparation method for nickel chromium-chromium carbide coating with high hardness and low porosity |
| CN106756713A (en) * | 2016-11-10 | 2017-05-31 | 哈尔滨工程大学 | Improve coating of combustion engine compressor drum barrel wearability peculiar to vessel and preparation method thereof |
| CN106929788A (en) * | 2017-05-02 | 2017-07-07 | 安徽威龙再制造科技股份有限公司 | A kind of multi-element alloy coat of sinking roller and its preparation and spraying method |
| CN109722618A (en) * | 2017-10-26 | 2019-05-07 | 沈阳黎明国际动力工业有限公司 | A kind of supersonic flame spraying technique of cobalt chromium tungsten wear-resistant coating |
| EP3904555A1 (en) * | 2018-12-29 | 2021-11-03 | Kunming University Of Science And Technology | Ultralimit alloy and preparation method therefor |
Non-Patent Citations (1)
| Title |
|---|
| 核阀密封面激光熔覆无钨低碳中钴合金粉末;金坤文等;金属热处理;第第39卷卷(第第2期期);77-80 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114318206A (en) | 2022-04-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Rhys-Jones | Thermally sprayed coating systems for surface protection and clearance control applications in aero engines | |
| CN107083502B (en) | Wear-resistant and corrosion-resistant cobalt-based alloy powder and application method thereof | |
| US7141110B2 (en) | Erosion resistant coatings and methods thereof | |
| EP1852520B1 (en) | Wear-resistant coating | |
| US9222164B2 (en) | Process for forming a chromium diffusion portion and articles made therefrom | |
| JPH04263058A (en) | Method for producing age hardening alloy coating based on chromium carbide-nickel and article with coating produced thereby | |
| CA2216068A1 (en) | Abradable seal assembly | |
| Rhys-Jones | The use of thermally sprayed coatings for compressor and turbine applications in aero engines | |
| CN108866470A (en) | A kind of preparation method of air plasma spraying alloy-ceramic laminar coating | |
| CN114318206B (en) | Wear-resistant coating for gas turbine crossfire tube and preparation method thereof | |
| Kingswell et al. | Optimizing the vacuum plasma spray deposition of metal, ceramic, and cermet coatings using designed experiments | |
| US20070218309A1 (en) | Sprayable composition | |
| US6815099B1 (en) | Wear resistant coating for brush seal applications | |
| Thorpe et al. | HVOF thermal spray technology | |
| CN117305748A (en) | High-temperature self-lubricating abradable seal coating and preparation method thereof | |
| WO1997019809A9 (en) | Thermal spray using adjusted nozzle | |
| CN112030097A (en) | High-temperature gradient sealing coating for gas turbine and preparation method thereof | |
| CA2547530C (en) | Running-in coating for gas turbines and method for production thereof | |
| CN110241352B (en) | Abrasion-resistant composite material for water turbine and preparation method and application thereof | |
| AU2002328738A1 (en) | Sprayable composition | |
| KR20000047670A (en) | Abradable material for labyrinth seals | |
| CN112779451B (en) | Chromium carbide metal ceramic composite powder, coating and preparation method thereof | |
| Tucker Jr | The use of thermal spray coatings for protection against wear and corrosion | |
| CN115679237A (en) | High-temperature abradable seal coating for rear case of aircraft engine | |
| CN113416912A (en) | Method for eliminating barrel adhesion of metal coating prepared by thermal spraying and improving coating performance |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |