CN208486915U - A kind of turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying - Google Patents
A kind of turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying Download PDFInfo
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- CN208486915U CN208486915U CN201820911736.8U CN201820911736U CN208486915U CN 208486915 U CN208486915 U CN 208486915U CN 201820911736 U CN201820911736 U CN 201820911736U CN 208486915 U CN208486915 U CN 208486915U
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- outer ring
- turbine outer
- temperature protection
- protection coating
- big thickness
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Abstract
The utility model provides a kind of turbine outer ring of big thickness high-temperature protection coating of inner-wall spraying, belongs to aero-engine technology field.The turbine outer ring includes superalloy turbine outer ring body and the MCrAlY high-temperature protection coating for being set to turbine outer ring body internal surface, and M is at least one of Ni and Co in MCrAlY.The high-temperature protection coating of the turbine outer ring has stronger coating cohesive strength, and, high temperature protection function admirable higher with the bond strength of matrix can effectively reduce damage of the turbine outer ring to blade when improper scraped finish occurs for turbine outer ring and blade tip.
Description
Technical field
The utility model relates to aero-engine technology fields, and the big thickness high temperature protection of in particular to a kind of inner-wall spraying
The turbine outer ring of coating.
Background technique
Power needed for aero-engine provides flight for aircraft is a kind of highly complex and accurate thermal machine.Hair
The core component of motivation includes air compressor, combustion chamber and turbine.Wherein, turbine includes turbine outer ring and turbine rotor leaf
Piece, rotor blade are set in the ring of turbine outer ring, inner wall of the blade tip towards turbine outer ring.The gas leakage of turbo blade blade tip
The influence measured to turbine efficiency is very big, and turbine efficiency directly influences the overall performance of engine.Turbine outer ring is as composition
The important component of engine gas runner can play the role of turbine blade-tip gap during control working condition.
Therefore, turbine outer ring need to possess good cooperation with turbo blade blade tip.Meanwhile turbine outer ring is directly fired with high temperature
Gas contact, environment temperature is higher, and operating condition is severe, has higher requirement for high-temperature behavior under service condition when long.
It is typically employed in the structure type of direct applying coating on turbine outer ring inner wall, however due to Long-term Vibration and high temperature
The erosion of corrosive medium and the larger easy stress of coating layer thickness are concentrated, and coated coating is caused to be easy chip off-falling.On the other hand, turbine
The improper scraping of outer ring and turbine rotor blade blade tip causes turbine blade-tip to seal so that turbine outer ring inside coating is easy to fall off
Tight effect decline, and turbine rotor blade can be damaged, to reduce engine performance, or even damage engine.
Utility model content
The purpose of this utility model includes providing a kind of turbine outer ring of big thickness high-temperature protection coating of inner-wall spraying, the whirlpool
The high-temperature protection coating for taking turns outer ring has stronger coating cohesive strength, high temperature protection performance higher with the bond strength of matrix
It is excellent, damage of the turbine outer ring to blade can be effectively reduced when improper scraped finish occurs for turbine outer ring and blade tip.
The utility model solves its technical problem using including following technical scheme to realize:
The utility model embodiment proposes a kind of turbine outer ring of big thickness high-temperature protection coating of inner-wall spraying, including height
Temperature alloy turbine outer ring ontology and be set to turbine outer ring ontology inner surface MCrAlY high-temperature protection coating, M in MCrAlY
For at least one of Ni and Co.
Further, in the utility model preferred embodiment, superalloy turbine outer ring body include the first noumenon with
And the second ontology for MCrAlY high-temperature protection coating to be arranged, the second ontology are set to the side of the first noumenon and to far from the
The direction of one ontology is protruded, and MCrAlY high-temperature protection coating is set to the surface of the side of the separate the first noumenon of the second ontology.
Further, in the utility model preferred embodiment, the side of the separate the first noumenon of the second ontology is equipped with recessed
Slot, MCrAlY high-temperature protection coating are set to groove.
Further, in the utility model preferred embodiment, groove includes the kerve being arranged radially along turbine outer ring
And the side channel being axially arranged along turbine outer ring, the junction of kerve and side channel are equipped with chamfering.
Further, in the utility model preferred embodiment, chamfering is in 30-60 °.
Further, in the utility model preferred embodiment, chamfering is in 30-45 °.
Further, in the utility model preferred embodiment, the side of the axial direction along turbine outer ring of the second ontology
Wall and the first noumenon form spraying transitional region.
Further, in the utility model preferred embodiment, MCrAlY high-temperature protection coating with a thickness of 0.8-
1.5mm。
Further, in the utility model preferred embodiment, the porosity < 5% of MCrAlY high-temperature protection coating.
Further, in the utility model preferred embodiment, outside the turbine of the big thickness high-temperature protection coating of inner-wall spraying
0.2 μm of the surface roughness Ra < of ring.
The beneficial effect of the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying includes: in the utility model embodiment
The turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying provided by the utility model embodiment has relatively strong
Coating cohesive strength, higher (intensity > 70MPa) with the bond strength of matrix, high temperature protection function admirable, porosity is moderate,
It can effectively reduce damage of the turbine outer ring to blade when improper scraped finish occurs for turbine outer ring and blade tip.
Detailed description of the invention
It, below will be to use required in embodiment in order to illustrate more clearly of the technical solution of the utility model embodiment
Attached drawing be briefly described, it should be understood that the following drawings illustrates only some embodiments of the utility model, therefore should not be by
Regard the restriction to range as, for those of ordinary skill in the art, without creative efforts, may be used also
To obtain other relevant attached drawings according to these attached drawings.
Fig. 1 is the cross section structure schematic diagram before not set groove of turbine outer ring provided by the embodiment of the utility model；
Fig. 2 is the cross section structure schematic diagram after groove is arranged of turbine outer ring provided by the embodiment of the utility model；
Fig. 3 is the cross section structure schematic diagram of turbine outer ring further groove provided by the embodiment of the utility model；
Fig. 4 is the section of the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying provided by the embodiment of the utility model
Structural schematic diagram.
Icon: 10- turbine outer ring；11- turbine outer ring ontology；111- the first noumenon；The second ontology of 112-；113- groove；
1131- kerve；1132- side channel；1133- chamfering；12- high-temperature protection coating；13- sprays transitional region.
Specific embodiment
It is practical new below in conjunction with this to keep the objectives, technical solutions, and advantages of the embodiments of the present invention clearer
Attached drawing in type embodiment, the technical scheme in the utility model embodiment is clearly and completely described, it is clear that is retouched
The embodiment stated is the utility model a part of the embodiment, instead of all the embodiments.Usually here in attached drawing description and
The component of the utility model embodiment shown can be arranged and be designed with a variety of different configurations.
Therefore, requirement is not intended to limit to the detailed description of the embodiments of the present invention provided in the accompanying drawings below
The scope of the utility model of protection, but it is merely representative of the selected embodiment of the utility model.Based in the utility model
Embodiment, every other embodiment obtained by those of ordinary skill in the art without making creative efforts, all
Belong to the range of the utility model protection.
In the description of the present invention, it should be noted that the orientation of the instructions such as term " on ", "lower", "inner", "outside"
Or positional relationship be based on the orientation or positional relationship shown in the drawings or the utility model product using when usually put
Orientation or positional relationship is merely for convenience of describing the present invention and simplifying the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as to the utility model
Limitation.In addition, term " first ", " second " etc. are only used for distinguishing description, it is not understood to indicate or imply relatively important
Property.
In addition, the terms such as term " vertical " are not offered as requiring component absolute upright, but can be slightly tilted.As " hung down
Directly " only refer to that its direction is more vertical with respect to for "horizontal", be not indicate the structure have to it is completely vertical, but can
To be slightly tilted.
In the description of the present invention, it should also be noted that, unless otherwise clearly defined and limited, term " is set
Set ", " installation ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.
For the ordinary skill in the art, it can understand above-mentioned term in the present invention with concrete condition
Concrete meaning.
It is specifically described with reference to embodiments.
Embodiment
The present embodiment provides a kind of turbine outer rings 10 of the big thickness high-temperature protection coating 12 of inner-wall spraying.Please refer to Fig. 1 extremely
Fig. 4, the turbine outer ring 10 of the above-mentioned big thickness high-temperature protection coating 12 of inner-wall spraying include 11 (base of superalloy turbine outer ring body
Body) and be set to turbine outer ring ontology 11 inner surface MCrAlY high-temperature protection coating 12.
Turbine outer ring ontology 11 uses wrought superalloy or cast superalloy, such as GH3536, the turbine outer ring sheet
Body 11 can be machined by forging.
In application scheme, please continue to refer to Fig. 4, superalloy turbine outer ring body 11 include the first noumenon 111 and
For the second ontology 112 of MCrAlY high-temperature protection coating 12 to be arranged.
Second ontology 112 is set to the side of the first noumenon 111 and protrudes to the direction far from the first noumenon 111,
MCrAlY high-temperature protection coating 12 is set to the surface of the side of the separate the first noumenon 111 of the second ontology 112.
Preferably, the side of the separate the first noumenon 111 of the second ontology 112 is equipped with groove 113, MCrAlY high temperature protection
(spraying) is arranged in groove 113 in coating 12.
Specifically, please in conjunction with Fig. 3, groove 113 includes kerve 1131 and the side channel 1132 connecting with kerve 1131,
Kerve 1131 is arranged radially along turbine outer ring 10, axial direction setting of the side channel 1132 along turbine outer ring 10.
In some preferred embodiments, the junction of kerve 1131 and side channel 1132 is equipped with chamfering 1133.
Preferably, above-mentioned chamfering 1133 for example can be in 30-60 ° (such as 30 °, 35 °, 55 ° or 60 °).More preferably, it is above-mentioned fall
Angle 1133 for example can be in 30-45 ° (such as 30 °, 40 ° or 45 °).
By the way that the chamfering 1133 of above-mentioned angular range is arranged, it can play a protective role to high-temperature protection coating 12, avoid side
Fiber stress concentration leads to coating cracking or even falls off.
Preferably, in application scheme, the side wall and first of the axial direction along turbine outer ring 10 of the second ontology 112
Body 111 forms spraying transitional region 13.The spraying transitional region 13 allows a small amount of spraying substance in spraying process to be sprayed at the area
Domain, to reduce the limitation in spraying process.
In application scheme, M is at least one of Ni and Co in the MCrAlY of MCrAlY high-temperature protection coating 12.Ni
Based alloy has the ability of excellent mitigation thermal stress, and Co base has excellent anti-oxidant and corrosive nature, the combination of Ni and Co
Coating is then set to have both above-mentioned characteristic.
It can refer to ground, MCrAlY high-temperature protection coating 12 for example can be CoNiCrAlY aerosolization spherical powder.
In some embodiments, the thickness of MCrAlY high-temperature protection coating 12 can be 0.8-1.5mm, such as
0.8mm, 0.9mm, 1.3mm, 1.4mm or 1.5mm.
In some preferred embodiments, the thickness of MCrAlY high-temperature protection coating 12 can be 1-1.2mm, such as
1mm, 1.1mm or 1.2mm.
By the structure design in application scheme, the thickness of MCrAlY high-temperature protection coating 12 can reach 1.5mm,
In the thickness range of 0.8-1.5mm, on the one hand can turbine outer ring 10 have good high temperature protection performance, on the other hand apply
There is stronger bond strength, the case where can reduce or avoid coating shedding between layer and turbine outer ring ontology 11.
Preferably, the MCrAlY high-temperature protection coating 12 of turbine outer ring 10 can be through atmospheric plasma side in application scheme
Method preparation, such as can refer to following manner: in spraying process, workpiece at the uniform velocity rotated with 200-400rpm (preferably 300rpm) with
Guarantee that the circle circumferential direction of turbine outer ring 10 has uniform thickness.
Spray gun and turbine outer ring 10 are moved up and down in 60 ± 5 ° of angles, every spraying 0.10-0.2mm, and spray gun is switched to pair
Position is claimed to be sprayed.Guarantee that turbine outer ring 10 is uniform perpendicular to the thickness of periphery direction coating by transformation Burners Positions
The coating quality of property and two end chamfer of spraying area, 1133 position.
When coating layer thickness reaches half (such as 0.5mm) of preset thickness, workpiece is placed in vacuum drying oven with 550-750 DEG C
Destressing, furnace cooling are played the role of in condition heat preservation 2-6h (such as 4h) of (such as 600 DEG C).
The blasting treatment of 60# corundum sand is utilized to the position of spray-on coating, blasting pressure for example can be 0.1-0.2MPa,
Then remaining sand grains or dust are blown off with compressed air.Continue spray-on coating to preset thickness and (corresponds to above-mentioned 0.5mm, herein
Preset thickness is 1.0mm).
Further, workpiece is placed in vacuum drying oven and is carried out with 900-1000 DEG C (such as 970 DEG C) of condition heat preservation 6-10h
DIFFUSION TREATMENT, with enhance coating cohesive strength and with the bond strength of matrix.
From the above, the atmospheric plasma method used is using plasma as heat source, it is ensured that powder is abundant in the jet
Melting.Spraying process is fully cooled using compressed air, can effectively prevent deformation caused by matrix overtemperature.
It is worth noting that preparing resulting MCrAlY high-temperature protection coating 12 with moderate hole by the above method
Rate (porosity < 5%), under the premise of possessing excellent high temperature protection performance, it is ensured that improper with blade tip generation
It is effectively reduced when scraped finish by the damage to blade.
By after coating spraying to certain thickness use vacuum heat treatment method go removing coating internal stress and being sprayed into it is pre-
If carrying out DIFFUSION TREATMENT after thickness, the cohesive strength of coating and the bond strength with matrix can be enhanced, reduce big thickness coatings by
Coating shedding risk caused by residual stress concentrations.
Preferably, before applying coating oil removing cleaning can be carried out to turbine outer ring 10, using frock clamp to non-spraying portion
It is protected position.
It spraying position and blasting treatment is carried out using 24# or 46# corundum sand, blasting pressure is controllable to 0.3-0.5MPa,
To remove the oxide layer of matrix surface, the surface state of clean, active and easy attachment is obtained, to increase surface-active simultaneously
Improve the bond strength between coating and matrix.
After blasting treatment, remaining sand grains or dust can be blown off with compressed air.
After spraying and heat treatment, the coating that machine add mode removal spraying transitional region 13 is adhered to can be used, it is then right
The coating of second ontology 112 carries out grinding and polishing treatment, keeps the surface of final products smooth, smooth, 0.2 μ of roughness Ra <
m。
Hardness>the 300HV0.3 for the MCrAlY high-temperature protection coating 12 that application scheme provides, porosity<5%, with matrix
Bond strength > 70MPa, function admirable.
To sum up, the turbine outer ring of the big thickness high-temperature protection coating 12 of inner-wall spraying provided by the utility model embodiment
10 have stronger coating cohesive strength, and higher with the bond strength of matrix, high temperature protection function admirable, porosity is moderate,
Occur to can effectively reduce damage of the turbine outer ring 10 to blade when improper scraped finish with blade tip.
The above is only the preferred embodiments of the utility model, are not intended to limit the utility model, for this field
Technical staff for, various modifications and changes may be made to the present invention.Within the spirit and principle of the utility model,
Any modification, equivalent replacement, improvement and so on should be included within the scope of protection of this utility model.
Claims (10)
1. a kind of turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying, which is characterized in that outside including superalloy turbine
Ring body and the MCrAlY high-temperature protection coating for being set to the turbine outer ring body internal surface, in the MCrAlY M be Ni and
At least one of Co.
2. the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying according to claim 1, which is characterized in that described
Superalloy turbine outer ring body includes the first noumenon and the second ontology for the MCrAlY high-temperature protection coating to be arranged,
Second ontology is set to the side of the first noumenon and protrudes to the direction far from the first noumenon, the MCrAlY
High-temperature protection coating is set to the surface of the side far from the first noumenon of second ontology.
3. the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying according to claim 2, which is characterized in that described
The side far from the first noumenon of second ontology is equipped with groove, and the MCrAlY high-temperature protection coating is set to described recessed
Slot.
4. the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying according to claim 3, which is characterized in that described
Groove includes the kerve being arranged radially along the turbine outer ring and the side channel being axially arranged along the turbine outer ring, described
The junction of kerve and the side channel is equipped with chamfering.
5. the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying according to claim 4, which is characterized in that described
Chamfering is in 30-60 °.
6. the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying according to claim 5, which is characterized in that described
Chamfering is in 30-45 °.
7. the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying according to claim 2, which is characterized in that described
The side wall and the first noumenon of the axial direction along the turbine outer ring of second ontology form spraying transitional region.
8. the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying according to claim 1, which is characterized in that described
MCrAlY high-temperature protection coating with a thickness of 0.8-1.5mm.
9. the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying according to claim 1, which is characterized in that described
The porosity < 5% of MCrAlY high-temperature protection coating.
10. the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying according to claim 1, which is characterized in that institute
0.2 μm of surface roughness Ra < for stating the turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820911736.8U CN208486915U (en) | 2018-06-12 | 2018-06-12 | A kind of turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820911736.8U CN208486915U (en) | 2018-06-12 | 2018-06-12 | A kind of turbine outer ring of the big thickness high-temperature protection coating of inner-wall spraying |
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| CN208486915U true CN208486915U (en) | 2019-02-12 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108642435A (en) * | 2018-08-07 | 2018-10-12 | 广东省新材料研究所 | A kind of big thickness high-temperature protection coating of turbine outer ring inner wall and preparation method thereof |
-
2018
- 2018-06-12 CN CN201820911736.8U patent/CN208486915U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108642435A (en) * | 2018-08-07 | 2018-10-12 | 广东省新材料研究所 | A kind of big thickness high-temperature protection coating of turbine outer ring inner wall and preparation method thereof |
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| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 510000 No. 363, Changxin Road, Guangzhou, Guangdong, Tianhe District Patentee after: Institute of new materials, Guangdong Academy of Sciences Address before: 510000 No. 363, Changxin Road, Guangzhou, Guangdong, Tianhe District Patentee before: GUANGDONG INSTITUTE OF NEW MATERIALS |
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| CP01 | Change in the name or title of a patent holder |