CN104975255B - Turbomachinery - Google Patents
Turbomachinery Download PDFInfo
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- CN104975255B CN104975255B CN201510442623.9A CN201510442623A CN104975255B CN 104975255 B CN104975255 B CN 104975255B CN 201510442623 A CN201510442623 A CN 201510442623A CN 104975255 B CN104975255 B CN 104975255B
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Abstract
The invention discloses a kind of turbomachinery, it is characterised in that coated with seal coating；The seal coating includes at least two sub- coatings, the respectively alloy-layer coated in matrix surface and the cermet coating coated in alloyed layer.Turbomachinery provided by the invention, its gap location are coated with seal coating.Under working condition, vane tip scraping seal coating, preferable radial air flow gap is formed, i.e. gap is minimum, so as to obtain maximum differential pressure, significantly improves mechanical efficiency, and energy consumption reduces, life.
Description
Technical field
The present invention relates to a kind of turbomachinery.
Background technology
With making rapid progress for science and technology, the requirement also more and more higher, while the theory of energy-conserving and environment-protective to mechanical efficiency
Also all the more go deep into product design and processing and manufacturing technology.In turbomachinery, the practicality and reliability of clearance seal for
Elevating mechanism efficiency, ensure that machine security operation, energy-conserving and environment-protective are all significant.With the turbocompressor in turbomachinery
Exemplified by, just develop towards the application direction of Large Copacity, high efficiency, high compression ratio.
As shown in figure 1, under working condition, the compressor blade 11 of compressor 1 12 rotates around the shaft, compressor blade 11
Gap between tip 13 and the inwall of casing 14 is smaller, and relative leakage amount (ratio of leakage rate and air inflow) is smaller, work effect
Rate is higher, and energy consumption is lower, and service life is longer.According to statistics, compressor radial clearance often increases 0.13mm, and unit consumption just increases
Add 0.5%；Conversely, radial clearance, per less 0.25mm, operating efficiency can improve 1%.Therefore, reduce in tip 13 and casing 14
Gap between wall, improve compression ratio, it has also become improve operating efficiency, save the customary means of energy consumption.The method for reducing gap
Have a variety of, the most widely used labyrinth sealing technology between level in industry, i.e., set several around rotating shaft 12 and arrange successively at present
The belt sealing tooth of row, a series of gaps of damming are formed between tooth and tooth and are passing through tortuous labyrinth with expansion cavity, compressed object
Gap when produce throttle effect and reach the purpose of Drain Resistance.But when compressed object is in high flow condition, and it is hard particles
During thing, heavy wear can be caused to seal, cause gap to become big, reduce Drain Resistance effect, so as to cause loss increase, unit effect
Rate reduces, and necessary maintenance down, influences to produce when serious.
The content of the invention
The invention aims to overcome deficiency of the prior art, there is provided what a kind of abradability can be high obturages painting
Layer.
To realize object above, the present invention is achieved through the following technical solutions：
Seal coating, it is characterised in that including at least two sub- coatings, respectively the alloy-layer coated in matrix surface and
Cermet coating coated in alloyed layer；The alloy-layer according to weight percent content by 30%~40% Co,
25%~35% Ni, 15%~25% Cr, 5%~10% Al, 0.5%~5% Y compositions；The cermet coating
According to weight percent content by 20%~25% BN, 23%~33% Co, 17%~27% Ni, 15%~25%
Cr, 4%~8% Al, 1%~2% Y compositions.
Preferably, porosity is no more than 15%.
Preferably, porosity is 10%~15%.
Preferably, pore diameter is not more than 25 μm.
Preferably, its case hardness is 60~80HR15Y.
Preferably, the bond strength of cermet coating is not less than 23MPa.
Preferably, the thickness of the alloy-layer is 50um~150um (preferably 100um).
Preferably, the thickness of the cermet coating is 400um~800um (preferably 600um).
Preferably, described matrix is turbomachinery.
Preferably, the turbomachinery is turbocompressor.
A kind of preparation method of seal coating that can be high it is a further object to provide abradability.
To achieve the above object, the present invention is achieved through the following technical solutions：
The preparation method of seal coating, it is characterised in that comprise the following steps：
A. spraying equipment is used, the alloy material that preparation is formed according to the element of the alloy-layer is sprayed into matrix table
Face, form the alloy-layer that thickness is 50um~150um (preferably 100um)；
B. spraying equipment is used, the cermet material that preparation is formed according to the element of the ceramic layer is sprayed into alloy
Layer surface, the cermet coating that thickness is 400um~800um (preferably 600um) is formed, it is final to be made coated in matrix surface
Seal coating.
Preferably, spraying is formed before alloy-layer, and matrix surface is pre-processed；Pretreatment includes cleaning and sandblasting
Processing；Matrix surface is checked after pretreatment；If detecting there is hole or impurity, it is necessary to which impurity is clear in matrix surface
Remove, and filled and led up hole by way of repair welding polishing.
Preferably, in the step a, sprayed using supersonic spray coating equipment.
Preferably, in the step b, sprayed using supersonic spray coating equipment.
Preferably, the step b also includes the matrix after spraying being placed on 300 DEG C~500 DEG C (preferably 400 DEG C)
Heat treatment 1~3 hour (preferably 2 hours) in environment.
It is a further object to provide a kind of high turbomachinery of mechanical efficiency.
To achieve the above object, the present invention is achieved through the following technical solutions：
Turbomachinery, it is characterised in that coated with seal coating.
Preferably, it is turbocompressor.
Seal coating provided by the invention, good abradability energy and anti-erosion property are had concurrently, suitable for turbomachinery
Sealing, the gap of turbomachinery can be reduced, reduce leakage rate, greatly improve the mechanical efficiency of turbomachinery.Except the effect of obturaging, envelope
Tight coating can also provide insulated heat for turbomachinery, avoid the generation of wild effect caused by high-temperature high-speed airflow.
Seal coating provided by the invention includes two layers of coatings, respectively the alloy-layer coated in matrix surface and is coated in
The cermet coating of alloyed layer.
Prime coat using alloy-layer as coating matrix surface, due to alloy-layer with matrix material in heat transfer, thermal expansion
Etc. matching in performance, there is good bond strength between matrix, it is ensured that coating is also without de- after matrix much time using
Fall, extend the service life of coating, reduce the frequency of maintenance of turbomachinery.
The obtained cermet material of ceramics is added in alloy, cermet material coated alloy layer forms cermet
Layer.Metallographic in cermet coating makes cermet coating have the corrosion resistance of metal, inoxidizability, especially has suitably hard
Degree, so as to possess erosion wear resistance, the impact of gap runner high speed air-flow, hard particles thing is resisted, avoids coating from damaging, extended
Coating service life, while gap can be avoided to become big, it ensure that sealing effectiveness.Ceramic phase in cermet makes cermet
The overall hardness of layer reduces compared with the hardness of simple metal, and shear strength and coefficient of friction also reduce, so as to it is good it is abradable,
Self-lubricating.When the cermet coating of the sophisticated scraping casing inner wall surface of compressor blade, due to cermet coating have it is good
Good abradability energy, coating is smaller to the impulsive force and frictional force of vane tip, coating by vane tip while scraping not
It can damage, coating extends the service life of turbomachinery also without coming off, and gap does not become big with the increase of run time, subtracts
Few leakage rate, improve the mechanical efficiency of turbomachinery.The addition of ceramic phase also makes cermet coating have high temperature resistant property.
The preparation method of seal coating provided by the invention, technique is simple, the seal coating reparation being prepared and performance
Adjustment is simple.
Turbomachinery provided by the invention, its gap location are coated with seal coating.Under working condition, vane tip scraping envelope
Tight coating, forming preferable radial air flow gap, i.e. gap is minimum, so as to obtain maximum differential pressure, significantly improves mechanical efficiency, and
Energy consumption reduces, life.
Brief description of the drawings
Fig. 1 is the cut-away view of traditional turbocompressor.
Fig. 2 is the cut-away view of the turbocompressor coated with seal coating in the embodiment of the present invention；
Fig. 3 be the average value of sliding wear extent of the seal coating of each embodiment, existing WC coatings sliding wear extent,
The curve map that the sliding wear extent of existing CrO coatings changes with wearing- in period；
Fig. 4 is the matrix surface of the seal coating coated with each embodiment in the environment of 200r/min erosion speed
The average value of unit area wear extent, the uncoated coating in surface matrix the curve that changes over time of unit area wear extent
Figure；
Fig. 5 is the matrix surface of the seal coating coated with each embodiment in the environment of 300r/min erosion speed
The average value of unit area wear extent, the uncoated coating in surface matrix the curve that changes over time of unit area wear extent
Figure.
Embodiment
The present invention is described in detail below in conjunction with the accompanying drawings：
As shown in Fig. 2 the cut-away view for turbocompressor.Seal coating 2 is coated with the inwall of casing 14.Obturage
Coating 2 includes two straton coatings, respectively coated in the alloy-layer 21 on the inwall of casing 14 and coated in the surface of alloy-layer 21
Cermet coating 22.Turbocompressor under working condition, its compressor blade 11 12 are rotated around the shaft, and sophisticated 13 scrapings are obturaged
The cermet coating 22 of coating 2, make the gap between compressor blade 11 and casing 14 minimum, reduce the leakage in compression process
Amount, the mechanical efficiency of turbocompressor is improved, reduce power consumption, increase the service life.
The component weight percent content of the alloy-layer 21 of seal coating 2 is as shown in Table 1 in each embodiment：
Table one
The component weight percent content of the cermet coating 22 of seal coating 2 is as shown in Table 2 in each embodiment：
Table two
The physical parameter of seal coating 2 and its cermet coating 22 is as shown in Table 3 in each embodiment：
Table three
By experimental results demonstrate porosity is not more than 15%, preferably 10%~15%, and pore diameter is no more than 25 μm
When, the abradability of seal coating 2 can be optimal with anti-erosion property.The case hardness (HR15Y) of seal coating is in 30-80 scopes
Interior, the bond strength of cermet coating is more than 7MPa, you can proving the abradability of seal coating can meet with anti-erosion property
Requirement.
The preparation method of seal coating, comprises the following steps：
A. first, the inwall of turbomachinery casing 14 is pre-processed；Pretreatment includes cleaning and blasting treatment.It is and right
Pretreated inwall is checked.If detecting there is hole or be mingled with, it is necessary to which impurity is removed, and is beaten by repair welding in inwall
The mode of mill fills and leads up hole.
Then, using supersonic spray coating equipment, alloy material is sprayed into the inwall of casing 14, forms 100um alloy
Layer 21.The weight percent content of alloy-layer each component is as shown in Table 1.
B. supersonic spray coating equipment is used, cermet material is sprayed into the surface of alloy-layer 21, forms 600um metals pottery
Enamel coating 22.The weight percent content of cermet coating each component is as shown in Table 2.The cermet coating 22 of formation, ceramic phase BN
It is uniformly filled in the skeleton that CoNiCrAlY metallographics are built, is formed in cermet coating 22 and be uniformly distributed hole, hole
The porosity of diameter and cermet coating 22 as shown in Table 3, so as to suitably reduce the hardness of cermet coating, makes metal make pottery
Enamel coating has abradability energy and anti-erosion property concurrently.If BN distributed mutuallies are uneven, intensive place, hardness is too low, causes coating surface shape
The defects of into pit, accelerate the abrasion of coating, sealing effectiveness declines；At missing, excessive high hardness, abradability can reduce, right
Vane tip causes to damage.
Matrix after spraying is placed in 400 DEG C of environment and is heat-treated 2 hours.Heat treatment can reduce the planted agent of coating
Power, the bond strength between alloy-layer and casing, cermet coating and alloy-layer is improved, avoid coating shedding, extension uses the longevity
Life.On the other hand, heat treatment can also improve distribution consistency degree of the BN phases in metallographic, further improve the performance of coating.
C. quality inspection is carried out to the coating after heat treatment.It is qualified to examine, and completes the spraying to turbocompressor, is made and applies
Overlay on the seal coating 2 of the inwall of casing 1.
Thermal shock resistance test is carried out to the coating in above example, comprised the following steps that：By predetermined time interval
Coating is exposed in flame or is placed in the stove for reaching design temperature, then naturally cooled to room temperature or blown with air cold
Coating switches coating to room temperature repeatedly between specified high temperature and low temperature, and record until needed for coating stripping repeatedly
Switching times, the thermal shock resistance of coating is evaluated according to coating damaged condition.The present embodiment is that coating is placed on into 760 DEG C
In heating furnace, be incubated 10 minutes, after take out quenching in 10-20 DEG C of water of input, after 5 times are amplified sem observation, place into heating
Quenching after stove heat, after so heating quenching 40 times repeatedly, coating is still excellent without stripping, thermal shock resistance.
The quality of the thermal shock resistance of coating is closely related with the bond strength of coating.The thermal shock resistance of coating is better,
The bond strength of coating is higher, conversely, the thermal shock resistance of coating is poorer, the bond strength of coating is lower.And the combination of coating
The height of intensity can indirectly prove the height of coating anti-erosion property, the height of abradability energy.That is coating
Bond strength is higher, coating anti-erosion property is higher, abradability can be higher, conversely, coating anti-erosion property is lower, abradable
Performance is lower.
Heat stability testing is carried out to the coating in above example, after being incubated 300 hours at 760 DEG C, tests its painting
The porosity of layer, pore diameter, case hardness and cermet coating bond strength change, as a result as shown in Table 4：
Table four
The data of the data of table four and table three are contrasted it can be found that coating is by (300 hours) for a long time
After high-temperature process (760 DEG C), porosity, case hardness, bond strength remain in that stabilization, illustrate the seal coating of the present invention and have
Preferable heat endurance, resistance to elevated temperatures are excellent.The case hardness and bond strength of seal coating keep stable, illustrate the present invention
Seal coating have preferable abradability energy.
Using friction wear testing machine to the seal coating of the above example with same thickness, existing WC coatings, existing
There are CrO coatings to carry out sliding wear testing, its abradability energy is evaluated by the sliding wear extent of seal coating.Seal coating
Sliding wear extent is bigger, and the abradability of seal coating can be higher.Sliding wear testing comprises the following steps that：
Wear test is carried out using MRH-3 high-speed loops block abrasion tester.To reduce wear area and abrasion width as far as possible
Influence to experimental result, improves the accuracy of experimental result, and wear rate uses two kinds of computational methods, i.e. area wear rate E and
Width wear rate E ＇, abradability energy RAR and RAR ＇ are respectively E and E ＇ inverse.
Wherein E=sliding abrasion quality/(effective wear area * times)；RAR=1/E；
E ＇=sliding abrasion quality/(effective abrasion width * times)；RAR=1/E ＇.
The sliding wear extent, existing of the average value of the sliding wear extent of the seal coating of above example, existing WC coatings
The curve map that the sliding wear extent of some CrO coatings changes with wearing- in period is as shown in Figure 3.
As seen from Figure 3, the sliding wear extent of seal coating of the invention is higher than existing WC coatings and CrO coatings
Wear extent is slid, that is, existing WC coatings and CrO coatings can be better than by illustrating the abradability of the seal coating of the present invention.The present invention
The sliding wear extent of seal coating can be higher than the sliding wear extent of existing WC coatings and CrO coatings higher than abradability, make
Compressor blade 11 can be engaged preferably after being rubbed with the seal coating 2 on the inwall of turbomachinery casing 14, so that calming the anger
The gap between seal coating 2 on machine blade 11 and the inwall of turbomachinery casing 14 minimizes, and reduces pressure to greatest extent
Leakage rate in compression process, the mechanical efficiency of turbocompressor is improved, reduce power consumption, increase the service life.
Utilize matrix of the erosion device to the seal coating coated with above example, the matrix row erosion wear resistance without coating
It can test, comprise the following steps that：Using MSH type grain-abrasion testing machines, river sand granularity is 30-70 mesh, with water by volume
5000：:2800 are mixed into mortar, and erosion angle is 90 °, and the erosion speed that 200r/min and 300r/min is respectively adopted is tried
Test.Weighed once every 30min, abrasion condition is characterized with unit area matrix surface wear extent：V=(m0-m1)/A.In formula：
V --- matrix unit area wear extent, m0 --- quality before abrasion, m1 --- quality after abrasion, A --- by erosion area.
In the environment of 200r/min erosion speed, the list of the matrix surface of the seal coating coated with above example
The plane product average value of wear extent, the uncoated coating in surface matrix unit area wear extent time history plot such as
Shown in Fig. 4.
In the environment of 300r/min erosion speed, the list of the matrix surface of the seal coating coated with above example
The plane product average value of wear extent, the uncoated coating in surface matrix unit area wear extent time history plot such as
Shown in Fig. 5.
From Fig. 4 and Fig. 5：The matrix of seal coating coated with above example, compared with the base of the uncoated coating in surface
The anti-erosion property of body improves.
The anti-erosion property of coating can be according to coating hardness come indirectly.The experience studied according to various countries, seal coating
The anti-erosion property of case hardness (HR15Y) i.e. explainable coating in the range of 30-80 is excellent.As shown in Table 3, it is of the invention
For seal coating case hardness (HR15Y) between 60-80, the seal coating of the indirect judgement present invention has excellent erosion wear resistance
Energy.
Embodiment in the present invention is only used for that the present invention will be described, and is not construed as limiting the scope of claims limitation,
Other substantially equivalent replacements that those skilled in that art are contemplated that, all fall in the scope of protection of the present invention.
Claims (7)
1. turbomachinery, it is characterised in that coated with seal coating；The seal coating includes at least two sub- coatings, respectively
For the alloy-layer coated in matrix surface and the cermet coating coated in alloyed layer；The alloy-layer is according to weight percent
Than content by 30%~40% Co, 25%~35% Ni, 15%~25% Cr, 5%~10% Al, 0.5%~5%
Y composition；The cermet coating is according to weight percent content by 20%~25% BN, 23%~33% Co, 17%
~27% Ni, 15%~25% Cr, 4%~8% Al, 1%~2% Y compositions；The porosity of the seal coating is
No more than 15%；The pore diameter of the seal coating is not more than 25 μm.
2. turbomachinery according to claim 1, it is characterised in that the porosity of the seal coating be 10%~
15%.
3. turbomachinery according to claim 1, it is characterised in that its case hardness of the seal coating be 60~
80HR15Y。
4. turbomachinery according to claim 1, it is characterised in that the bond strength of the cermet coating is not less than
23MPa。
5. turbomachinery according to claim 1, it is characterised in that the thickness of the alloy-layer is 50 μm~150 μm
。
6. turbomachinery according to claim 1, it is characterised in that the thickness of the cermet coating be 400 μm~
800μ m 。
7. turbomachinery according to claim 1, it is characterised in that be turbocompressor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510442623.9A CN104975255B (en) | 2014-08-29 | 2015-07-24 | Turbomachinery |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410438995 | 2014-08-29 | ||
| CN201410438995X | 2014-08-29 | ||
| CN201510442623.9A CN104975255B (en) | 2014-08-29 | 2015-07-24 | Turbomachinery |
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| Publication Number | Publication Date |
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| CN104975255A CN104975255A (en) | 2015-10-14 |
| CN104975255B true CN104975255B (en) | 2018-04-03 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110257813A (en) * | 2019-07-10 | 2019-09-20 | 上海君山表面技术工程股份有限公司 | Antioxidant wear-resistant composite coating |
| CN110821837A (en) * | 2019-12-12 | 2020-02-21 | 国家能源蓬莱发电有限公司 | Slurry pump |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE102005041003A1 (en) * | 2005-08-29 | 2007-03-01 | Man Turbo Ag | Shaft seal for e.g. single shaft expander, of transmission machine, has ring chamber facing interior of expander and provided with supply of sealing gas, and another chamber turned away to interior and provided with extraction of gas |
| CN101653998A (en) * | 2009-09-18 | 2010-02-24 | 武汉理工大学 | High-temperature abradable seal coating |
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