CN1189195A - Metal component with a high-temp. protection coating system and method of coating thereof - Google Patents
Metal component with a high-temp. protection coating system and method of coating thereof Download PDFInfo
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- CN1189195A CN1189195A CN96195014A CN96195014A CN1189195A CN 1189195 A CN1189195 A CN 1189195A CN 96195014 A CN96195014 A CN 96195014A CN 96195014 A CN96195014 A CN 96195014A CN 1189195 A CN1189195 A CN 1189195A
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Abstract
A metal substrate has a protective coating system applied on an outer surface thereof. The coating system includes an alloy layer placed on the outer surface. The alloy layer has a polished surface facing away from the outer surface. A substantially uniformly thick aluminide layer is placed on the alloy layer. A ceramic layer placed on the aluminide layer forms a thermal barrier layer. The coating process includes steps such as: placing the alloy layer on the outer surface of the body; polishing the alloy layer; placing the aluminide layer having a substantially uniform thickness on the alloy layer; and placing the ceramic layer on the aluminide layer.
Description
The present invention relates to have the hardware and the coating method thereof of high temperature protection coat system.
U.S. Patent No. 3,873,347 (Walker etc.) and U.S. Patent No. 3,874,901 (Rairden) have disclosed a kind of by providing a kind of coat system of body to improve Ni-based or cobalt-base superalloy body (body), the especially method of the resistance to high temperature oxidation of gas turbine member and corrosion resistance nature.This method is made up of the following step: the alloy layer that one deck now is called the MCrAlY alloy at first is set on body; Apply one deck aluminide then thereon; Then, heat the body of above-mentioned coating, make the aluminium mutual diffusion enter alloy layer according to U.S. Patent No. 3,874,901.The raising of corrosion-resistant and resistance of oxidation mainly is the contribution of aluminide, and this is because aluminide has increased the content of aluminium in the coat system.
U.S. Patent No. s.4,055,705 (people such as Stecura); 4,321,310 (people such as Ulion); With 4,321,311 (Strangman) have disclosed a kind of can be used for by coat system Ni-based or the gas turbine member that cobalt-base superalloy is made.Described coat system is in substrate surface one bonding coat to be set earlier, then the insulating ceramic sheet, especially has the ceramic layer of columnar grain structure, is placed on the bonding coat, and thermal insulation layer is bonded in the basic unit.Bonding coat is made by the MCrAlY alloy, promptly contains the alloy of chromium, aluminium and rare earth metal such as yttrium in basal component, and basal component comprises a kind of iron, cobalt and nickel at least.Below these elements, also can add in the MCrAlY alloy.A key property of bonding coat is to form on the MCrAlY alloy, and is used for aluminum oxide thin layer that thermal insulation layer " anchor " is lived.
U.S. Patent No. 5,238,752 (people such as Duderstadt) have disclosed a kind of coat system that is used for the gas turbine member.This system also comprises ceramic insulation layer and the bonding coat that thermal insulation layer and basic unit are bonded together.Bonding coat is to be made by the intermetallics of aluminium, especially nickel aluminide or platinum aluminide.Bonding coat also is an alumina layer, is used for bonding thermal insulation layer.
U.S. Patent No. 5,262,245 people such as () Ulion have disclosed without bonding coat, and simplify the experimental result that the coat system that contains thermal insulation layer is used for the gas turbine member.For this reason, disclosed a kind of superalloy compositions, it can make the basic unit of gas turbine member, and through after certain processing, forms alumina layer at its outside surface.This alumina layer is used for the ceramic insulation layer above it is sticked together.Bonding coat needn't be set between basic unit and thermal insulation layer specially.
United States Patent (USP) 5,087,477 (people such as Giggins) have reported a kind of physical gas phase deposition technology of using, and the method for ceramic insulation layer is set on the gas turbine member.This method comprises with electron beam makes the compound volatilization that generates thermal insulation layer, and to form the content of oxygen wherein on member be that a kind of atmosphere that can control is to accept thermal insulation layer.
United States Patent(USP) Nos. 5,154,885; 5,268,238; 5,273,712; With 5,401,307 (people such as Czech) have disclosed a kind of advanced coat system that is used for the gas turbine member.This member comprises MCrAlY alloy protecting coating.Disclosed MCrAlY alloy has meticulous isostatic and forms, and it can provide fabulous erosion resistance and resistance of oxidation, and for the superalloy as basic unit, extraordinary consistency is arranged.The main component of MCrAlY alloy is nickel and/or cobalt.Can add the other element, especially silicon and rhenium, this also discusses in patent.Especially rhenium shows it is extraordinary additive.Shown whole MCrAlY alloys all are suitable as the bonding coat of thermal insulation layer, especially hereinafter under the situation of described invention very much.
The member of gas turbine, as blade, impeller and heat shield element comprise with metal such as body Ni-based or that cobalt-base superalloy is made.Their expose portion usually applies the coat system that comprises protective coating, with the corrosion that prevents to cause owing to the oxygenizement under the high temperature and sulfuration.As described in the above-mentioned prior art document, be arranged on the coat system of body outside surface, comprise alloy layer and a ceramic insulation layer that is positioned on its alloy layer of constituting by the MCrAlY alloy.
In operation process, keep the gas turbine component inside of strong load effect, the internal passages that imports cold fluid is all arranged usually.The passage generally fixed position when its component operation has the one-level opening, disposes many secondary openings and be exposed in operation along the efficient part in the effusive air-flow of member.Cold fluid finally on the efficient part surface of member, forms a freezing mask, prevents that member from directly contacting with combustion gas, and cold fluid mixes with air-flow by the secondary opening afterwards.
Gas turbine member internal body passage might stand corrosion or oxidation etch, and this is because the temperature of the internal surface that the body interior passageway is limited still might be quite high.Therefore, accelerated at the fluid components of the passage of flowing through and the chemical reaction between the organism material.From the viewpoint of practicality, even fluid is air or air and steam mixture, so airborne impurity, ammonia and/or sulphur compound as in salt in the ocean environment or the rural environment all can produce corrosion.As a kind of anti-corrosion measure,, one deck aluminide is set all usually at the internal surface of gas turbine member interior passageway.
When making the gas turbine member, the outside surface of member is provided with alloy layer and ceramic layer, and internal surface is provided with aluminium compound layer, and operation must be careful, between the component that prevents the appearance surface coatings system, deleterious interaction takes place.Especially serious is at inner surface of component, and the aluminide by gas phase is aluminized and formed also can be deposited on the outside surface of member.General way is earlier alloy layer to be arranged on outside surface, before internal surface is aluminized, still keeps its original uneven surface.Aluminize at internal surface then, alloy layer also is coated with aluminium inevitably.Then,, grind or polish, to reach desired surfaceness on the alloy layer surface that is coated with aluminium.This treatment process has been removed the most aluminium compound layer of alloy surface, but never is whole.Like this, ceramic layer just is placed on a uncertain surface of chemical ingredients, thereby the intensity of resulting ceramic layer is suspectable.From the alloy layer surface, remove aluminide fully, need more complicated step, will strengthen manufacturing cost.
As a kind of alternative method of above-mentioned coating processes, the someone imagines, and before the outside surface of gas turbine component is provided with alloy layer, at the surfaces externally and internally of member one aluminium compound layer is set earlier all.Yet, in this case,, in the member body, formed the fragility phase of a rich aluminium owing to the diffusion of a large amount of aluminium that exist.The embrittlement of fragility mutual-assistance body falls under suspicion its use properties.
Therefore, the purpose of this invention is to provide a kind of hardware with high temperature protection coat system, and the method that applies this member.This method has overcome the equipment of above-mentioned general type and the deficiency of method, and can satisfy existing coat system is carried out improved demand.This method makes coat system and predetermined function thereof, and aluminium compound layer is had than Wheat Protein.If only have interactional words any time between aluminium compound layer and coat system, the method for this patent can not be subjected to the application of these aluminium compound layers and the restriction of position to be more suitable for using together with aluminium compound layer so.
According to the present invention, in order to reach the above-mentioned target that reaches other, provide a kind of method that applies at the outside surface of metallic article body, this method comprises following these steps:
Outside surface at body is provided with an alloy layer;
Alloy layer is polished;
The very uniform aluminium compound layer of an additional thickness on alloy layer;
Additional again ceramic layer on aluminium compound layer.
According to other mode of the present invention, the step that alloy layer is set comprises: only at outside surface alloy layer is set; The operation of aluminium compound layer is set, is also included within the internal surface that passage limits that forms in the body aluminium compound layer is set.
According to additional modes of the present invention, the operation that aluminium compound layer is set comprises: form an aluminium compound layer at internal surface, its thickness is up to 50 μ m; Form an aluminium compound layer on alloy layer, thickness is up to 10 μ m.
According to another pattern of the present invention, in placing operation, aluminium compound layer is polished.Aluminium compound layer can be provided with by the gas phase operation of aluminizing.
The pattern further according to the present invention, this method is included in and is provided with before the ceramic layer, to the aluminium compound layer step of polishing on the alloy layer.
According to adjoint mode of the present invention, alloy layer is carried out step of polishing, comprise the alloy layer of a surface roughness Ra less than 2 μ m is provided.Ra is measuring of spending of the injustice (put in order) on surface, measures with standard method.Particularly Ra is performed as follows mensuration: on a surface to be measured, delimit the reference line that length is suitable earlier.Along reference line, determine the smooth profile figure on surface with least square fitting method.Ra is a real surface and absolute value along the smooth surface deviation of reference line, calculates through arithmetical mean.The necessary sufficiently long of reference line, with the influence of elimination statistical fluctuation to the Ra value, and reference line again must be enough short, to keep implication that its is represented as whole surface.
According to the present invention, in order to reach above-mentioned and other target, provide a kind of product, this product comprises metal-based layer with outside surface and application system on the outer surface, this application system comprises:
The alloy layer of She Zhiing on the outer surface, alloy layer has polished surface back to outside surface;
Cover the aluminium compound layer on the alloy layer, and aluminium compound layer thickness is even; With
On aluminium compound layer, the ceramic layer of setting.
The preferred thickness of aluminium compound layer is less than 10 μ m.The surfaceness of the alloy layer that adjoins with aluminium compound layer, preferred value is less than 2 μ m.
Characteristic according to another preferred, alloy layer are to be formed and metal-based layer is Ni-based or cobalt-base superalloy by the MCrAlY alloy.Bells and whistles according to another preferred, aluminium compound layer is made up of compounds such as aluminium, nickel aluminide and platinum aluminides basically.
According to bells and whistles of the present invention, internal body forms passage, thereby defines the internal surface of body, and aluminium compound layer is arranged on the internal surface, and the thickness of aluminium compound layer is less than 50 μ m on the preferred internal surface.Aluminium compound layer is formed by aluminium, nickel aluminide or platinum aluminide.
According to further characteristic of the present invention, body and coat system have been formed the member of a gas turbine jointly.The gas turbine member can be the shape of fin, when it is included in the gas turbine running, is exposed to along tab portion in the effusive air-flow of goods, and tab portion is coated with coat system.
According to accompanying characteristics of the present invention, at internal body a passage is arranged, extend to tab portion always, and define the body internal surface, one deck aluminium compound layer is arranged on its internal surface.
Other characteristics of the present invention will be stated in additional claims.
Though the present invention with specific embodiments, has done detailed explanation to hardware and coating method aspect thereof with high temperature protection coating; Yet be not limited to the content explained,, and all fall within the scope suitable with claim of the present invention because in not breaking away from spiritual scope of the present invention, the variation of various improvement and structure all may occur.
Yet structure of the present invention and additional purpose and advantage thereof from the explanation and accompanying drawing of following special embodiment, can obtain the most thorough understanding.
Fig. 1 is the part of the cross-sectional view of the coat system that uses among the present invention.Fig. 2 is the sectional view of combustion steam turbine engine tab member, and it comprises basic unit and protective coating system as shown in Figure 1.
Consult accompanying drawing now.At first, especially with reference to figure 1, as can be seen from Fig. 1, a protective coating system is arranged on basic unit, this system comprises alloy layer, aluminium compound layer and the ceramic layer above it, and one deck aluminium compound layer on the internal surface of passage.
Basic unit 1 is the main body of product, gas turbine member especially, and in the running, it is standing the effect of strong thermal load, also stands the corrosive infringement simultaneously.Constitute the material of basic unit 1,, need possess intensity and stability of structure when the mechanical load that stands heat-flash load and additional force for example during centrifugal force.Ni-based or cobalt-base superalloy is to gain recognition widely, and obtains the material of manufacturing gas turbine used.For the thermal load of restriction to the basic unit 1, be provided with a coat system above.This coat system protection matrix 1 is not corroded it, comprising the erosion that causes owing to oxygenizement.This coat system comprises alloy layer 2, places the aluminide 3 on the alloy layer and places ceramic layer 4 on the aluminium compound layer 3, and alloy layer 2 is by the MCrAlY alloy composition, preferably as above-mentioned people such as Czech at United States Patent(USP) Nos. 5,154,885,5,268,238; 5,273,712 and 5,401,307 described the sort of MCrAlY alloys.These patents are incorporated herein by reference.Ceramic layer 4 is made by the columnar grain pottery, is made up of zirconium dioxide stabilization or partially stabilizedization especially basically.
A passage 5 is arranged in basic unit 1, and cold fluid therefrom flows through during the gas turbine running, makes basic unit's 1 cooling.Passage adjoins mutually with inwall 6, and an aluminium compound layer 7 is set on inwall 6.
2,3,4 and 7 layers setting is to finish according to specific program, with avoid 2,3,4 and 7 and form between, deleterious interaction takes place.The particularly important is aluminium compound layer 3 and 7.Aluminium compound layer 7 on the inwall 6 is to be used for specially protecting inwall 6, and it is not corroded.The aluminium compound layer 3 of passage 5 outsides for the function of coat system, may be unnecessary.Yet it is to apply on the inwall 6 in the process of aluminium compound layer 7, inevitably by product.
For aluminium compound layer 3 is combined in the functional coat system, and between alloy layer of avoiding any rough sledding of producing owing to its existence, aluminium compound layer 3 to be placed on placing and polished 2 and the ceramic layer 4 to be placed subsequently.The polished surface of alloy layer 2 is the smooth interface between alloy layer and the aluminium compound layer 3.The aluminium compound layer surface can be polished or be carried out surface treatment, comes as required to determine.The thickness of aluminium compound layer 3 preferably is controlled at below the 10 μ m, after advantageously placing, its surface is polished., also preferably before aluminium compound layer 3 is set, alloy layer 2 is polished for this reason, make its surfaceness less than 2 μ m.
The thickness of the aluminium compound layer 7 on the internal surface can be regulated, and itself and this layer functional performance is adapted.The preferred thickness of aluminium compound layer 7 is less than 50 μ m.
Aluminium compound layer 3 and 7 material are selected strict especially, preferably aluminium, nickel aluminide and platinum aluminide.Aluminium compound layer 3 and 7 is aluminized and can be applied easily with gas phase.This technology is known, and often be used in the prior art.But this method also can be splashed to the position that does not need to apply to aluminide to get on.Otherwise, as disclosing, need take special measure here.Coated alloy layer 2, not strict usually.Generally be to use plasma spraying process, this method is compared with being used for aluminized vapour phase processes, has stronger selectivity for position to be coated, does not generally have specific question.Best, coated alloy layer 2 needs special thermal treatment, so that alloy layer 2 is fixed in the basic unit 1 equably.
Aluminium compound layer 3 is set between alloy layer 2 and ceramic layer 4 an incidental benefit is arranged; providing can be to the aluminium source of alloy layer 2 diffusions; increased the required protective value of alloy layer; and provide an interface; under suitable condition; it can form a thin alumina layer, and it is the fixing best mode of ceramic layer.Yet for fear of owing to the too high alloy layer that the occurs 2 embrittlement problems of aluminium content, the thickness of aluminium compound layer 3 should be too not thick, and the thickness of aluminium compound layer just is considered to effective in the scope of 10 μ m usually.
Fig. 2 shows the member of whole gas turbine, and promptly blade 8.This member 8 has an airfoil section 9 (when this part 9 is the internal combustion turbine running " effectively parts ", standing impact) along its airflow flowing, fixing part 10 is (in the gas turbine operation process, member 6 anchored in place are thereon), hermetic unit 11 (its effect is to prevent the predefined flow path of flow shedding).Fig. 1 is the sectional view that obtains from the I-I position.
In order to make gas turbine blade 8 coolings, blade interior has a passage 5, and cold fluid therefrom passes through, as shown in Figure 1.Cold fluid is normally in fixed position 10 places charging, and is as shown in arrow 2.Cold fluid leaves gas turbine blade 8 by aperture 13, imports in airfoil section 9 airflow flowing.
As mentioned above, in the process that coat system is coated on the gas turbine blade 8, need special concern aperture 13, at applying coating 2,3,4 with prevented by clogged with material at 7 o'clock.Coated alloy layer 2 and ceramic layer 4 are strict usually.Therefore, after having applied coating 2,3,4 or 7, check preferably whether aperture 13 is blocked.Aperture 13 be coating 2,3,4 and 7 at least some applied finish after, hole again.Aperture 13 has preferably applied at alloy layer 2, but when not polishing as yet, makes with laser milling (Laser milling) or with electrification processing (ECM).
After applying aluminium compound layer 3 and 7, if necessary, can insert the throttling sheet and be fixed in the passage 5.Final thermal treatment in the polishing process in particular for ceramic layer 4, is a favourable procedure.
Claims (20)
1. the method for the outside surface of metallizing product body, this method comprises following operation:
Outside surface at body is provided with an alloy layer, and alloy layer is polished;
On alloy layer, a uniform aluminium compound layer of thickness is set; And
A ceramic layer is set on aluminium compound layer.
2. according to the method for claim 1, have a passage in the body at least, this passage defines the internal surface of body; The operation of alloy layer is set, only comprises alloy layer being set at outside surface; The operation of aluminium compound layer is set, comprises at internal surface aluminium compound layer being set simultaneously.
3. according to the method for claim 2, the operation that aluminide wherein is set comprises:
Constitute an aluminium compound layer at internal surface, its thickness is up to 50 μ m; Constitute an aluminium compound layer on alloy layer, its thickness is up to 10 μ m.
4. according to the method for claim 3, the operation that aluminium compound layer wherein is set comprises polishes the aluminium compound layer on the alloy layer.
5. according to the method for one of claim 1-4, the operation that aluminium compound layer wherein is set comprises that gas phase aluminizes.
6. according to the process of claim 1 wherein that the operation that aluminium compound layer is set comprises that gas phase aluminizes.
7. according to the method for one of aforesaid right requirement, it is included in and is provided with before the ceramic layer, and the aluminide that is positioned on the alloy layer is polished.
8. according to the method for one of aforesaid right requirement, wherein the technology that alloy is polished comprises the alloy layer of a surface roughness Ra less than 2 μ m is provided.
9. goods comprise the metal-based layer and the coat system on said outside surface that limit the body with outside surface; Above-mentioned coat system comprises: at the alloy layer that described outside surface is provided with, this alloy layer has a polished surface back to described outside surface; The basic aluminium compound layer uniformly of the thickness that on above-mentioned alloy layer, is provided with, and the ceramic layer that on aluminium compound layer, is provided with.
10. according to the goods of claim 9, wherein said aluminium compound layer thickness is less than 10 μ m.
11. according to the goods of claim 9 or 10, the alloy layer that adjoins mutually with described aluminium compound layer wherein, surfaceness is less than 2 μ m.
12. according to the goods of one of claim 9-11, wherein above-mentioned alloy layer is formed by the MCrAlY alloy.
13. according to the goods of one of claim 9-12, wherein said metal-based layer is Ni-based or cobalt-base superalloy.
14. according to the goods of one of claim 9-13, wherein said aluminium compound layer is made up of the compound that is selected from aluminium, nickel aluminide and platinum aluminide basically.
15. according to the goods of one of claim 9-14, in the wherein above-mentioned body passage is arranged, this passage defines the internal surface of this body; On this internal surface, be provided with an aluminium compound layer.
16. according to the goods of claim 15, wherein the thickness of the aluminium compound layer on internal surface is less than 50 μ m.
17., wherein, form by the compound that is selected from aluminium, nickel aluminide and platinum aluminide basically at the aluminium compound layer and the aluminium compound layer that is positioned at this internal surface of this outside surface according to the goods of claim 15 or 16.
18. according to the goods of one of claim 9-17, wherein said body and coat system have been formed the member of gas turbine.
19. according to the goods of claim 18, gas turbine member wherein is an aerofoil profile part, this member has comprised in the gas turbine operation process, exposes along the airfoil section in the goods airflow flowing; This airfoil section has applied above-mentioned coat system.
20. according to the goods of claim 19, wherein the inside of this body is formed with passage, this passage one has one deck aluminide extending to airfoil section and having delimited the internal surface of this main body on this internal surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN96195014A CN1189195A (en) | 1995-04-27 | 1996-04-15 | Metal component with a high-temp. protection coating system and method of coating thereof |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US08/432,432 | 1995-04-27 | ||
| CN96195014A CN1189195A (en) | 1995-04-27 | 1996-04-15 | Metal component with a high-temp. protection coating system and method of coating thereof |
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| CN1189195A true CN1189195A (en) | 1998-07-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN96195014A Pending CN1189195A (en) | 1995-04-27 | 1996-04-15 | Metal component with a high-temp. protection coating system and method of coating thereof |
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| CN (1) | CN1189195A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102933797A (en) * | 2010-06-03 | 2013-02-13 | 斯奈克玛 | Measuring the damage to a turbine-blade thermal barrier |
| CN109136849A (en) * | 2018-08-21 | 2019-01-04 | 中国科学院金属研究所 | A kind of gradient Al coating and preparation method thereof that Pt is modified |
-
1996
- 1996-04-15 CN CN96195014A patent/CN1189195A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102933797A (en) * | 2010-06-03 | 2013-02-13 | 斯奈克玛 | Measuring the damage to a turbine-blade thermal barrier |
| CN102933797B (en) * | 2010-06-03 | 2015-08-05 | 斯奈克玛 | Measure the infringement of turbine blade thermal-protective coating |
| CN109136849A (en) * | 2018-08-21 | 2019-01-04 | 中国科学院金属研究所 | A kind of gradient Al coating and preparation method thereof that Pt is modified |
| CN109136849B (en) * | 2018-08-21 | 2021-01-26 | 中国科学院金属研究所 | Pt-modified gradient Al coating and preparation method thereof |
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