CN206513407U - A kind of turbine rotor blade and the engine with it - Google Patents
A kind of turbine rotor blade and the engine with it Download PDFInfo
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- CN206513407U CN206513407U CN201720084201.3U CN201720084201U CN206513407U CN 206513407 U CN206513407 U CN 206513407U CN 201720084201 U CN201720084201 U CN 201720084201U CN 206513407 U CN206513407 U CN 206513407U
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- blade
- turbine rotor
- rotor blade
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- cavity
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Abstract
The utility model discloses a kind of turbine rotor blade and the engine with it, it is related to technical field of engines.The turbine rotor blade (1) is cast using Ni-based directionally solidified superalloy, DS superalloy, the blade (1) is cavity structure, there is the first anticorrosive coat (11) in the inner surface setting of cavity, the outer surface of the blade (1) is provided with the second anticorrosive coat (12).The engine includes turbine rotor blade as described above.The utility model has the advantage of：Turbine rotor blade of the present utility model is cast using Ni-based directionally solidified superalloy, DS superalloy, nickel base superalloy has preferable corrosion and heat resistant ability in itself, using directional solidification casting, relative to routine casting mode, the heat and corrosion resistant ability of blade not only greatly improved, and thermal fatigue life, creep rupture strength and creep strength all increase significantly；The outer surface of blade and cavity inner surface are provided with anticorrosive coat, improve the resistance to corrosion of blade, improve blade performance and life-span.
Description
Technical field
The utility model is related to technical field of engines, and in particular to a kind of turbine rotor blade and starting with it
Machine.
Background technology
Aero-engine includes compressor, combustion chamber and the big part of turbine three.The aeroplane engine used under marine environment
Machine turbine part, particularly turbine rotor blade, condition of work very severe.First, in order to pursue performance, turbine inlet temperature (TIT)
Constantly lifting, turbine rotor blade works under high temperature, high pressure, high rotating speed, it may occur however that fatigue and ablation equivalent damage.It is more important
, under marine environment, high humidity, salt fog content are high, fuel oil contains more impurity so that blade surface is under cryogenic
Electrochemical corrosion occurs through moisture, in blade surface formation corrosion pit；At high temperature due in salt fog and combustion product
Impurity produces strong heat erosion in blade surface, reduces the corrosion resistance of blade base alloy.Corrode makes to the safety of blade
With very harmful, the degree of injury of blade is seriously exacerbated, the reliability and service life of engine is directly affected.
For the aero-turbine rotor blade used under marine environment, mainly there are 3 kinds of measures at present：Engine is determined
Phase cleaning, blade use corrosion-resistant material, blade surface coating treatment.Turbine part mainly uses liquid ceanser when cleaning,
Under idling rating, cleaning agent is sprayed at fuel nozzle, the high temperature runner elements such as turbo blade are cleaned.Pass through engine
Although periodic cleaning is more effective to desalination, the simply ancillary method of periodicity, and can not thorough desalination, during with work
Between growth corrosion phenomenon still occurs.Due to the difference of alloying component, the heat erosion peak value focus temperature of various high temperature alloys
Degree is different；Due to material and the difference of manufacturing process, the mechanical property of blade also has larger difference, therefore comprehensive during selection material
Close and consider material property, operating temperature, manufacturing process and cost.It is isometric that current turbine rotor blade is generally nickel base superalloy
Crystalline substance casting, with certain anti-oxidant, corrosion resistance, but can not fully meet long-term use needs under marine environment.
Blade surface uses calorized coating, MCrAlY multi-element coatings, can effectively improve anti-oxidant, the corrosion resistance of blade, still
Life-span is shorter.With the growth of use time, coating is directly exposed in high-temperature fuel gas, and Al elements, which gradually exhaust, causes coating to lose
Effect.
Utility model content
The purpose of this utility model is to provide a kind of turbine rotor blade and the engine with it, to solve or at least subtract
Gently at least one in the presence of background technology the problem of.
The technical solution adopted in the utility model is：A kind of turbine rotor blade is provided, blade uses Ni-based directional solidification
High temperature alloy is cast, and the blade is cavity structure, has the first anticorrosive coat, the appearance of the blade in the inner surface setting of cavity
Face is provided with the second anticorrosive coat.
Preferably, first anticorrosive coat is the infiltration layer for including aluminium element silicon, and the thickness of infiltration layer is 0.02~0.1mm.
Preferably, second anticorrosive coat sprays the thermal barrier coating of double-decker, including one by way of thermal spraying
Metal adhesion layer and a ceramic layer, the metal adhesion layer are contacted with the outer surface of the blade, and the ceramic layer is sprayed on
The outside of the metal adhesion layer.
Preferably, the material of the ceramic layer is ZrO2Ceramics, are sprayed by the way of electro beam physics vapor phase deposition.
Preferably, the thickness of the ceramic layer is 0.05~0.25mm.
Preferably, the material of the metal adhesion layer is CoCrAlY, the thickness of the metal adhesion layer for 0.03~
0.2mm。
Preferably, the cavity is provided with multiple cold air paths by being divided into every rib on multiple unit cavitys, tenon, institute
Cold air path is stated to connect with the unit cavity.
Preferably, the leading edge of the blade is provided with multiple air film holes, and the air film hole connects the outer surface of the blade
And unit cavity；The trailing edge of the blade is provided with multiple coolings and splits seam, and seam is split in the cooling to be used for the unit air intracavitary
Cold air be drained to the trailing edge surface.
The utility model additionally provides a kind of engine, and the engine includes turbine rotor blade as described above.
The beneficial effects of the utility model are：
Turbine rotor blade of the present utility model is cast using Ni-based directionally solidified superalloy, DS superalloy, and nickel base superalloy is in itself
With preferable corrosion and heat resistant ability, using directional solidification casting, relative to routine casting mode, leaf not only greatly improved
The heat and corrosion resistant ability of piece, and thermal fatigue life, creep rupture strength and creep strength all increase significantly.
The cavity inner surface of blade forms a very thin element silicon containing aluminium in blade inner chamber by way of Al-Si co-infiltrating
Infiltration layer, the formation direction of infiltration layer be from inwall towards blade inside, its presence can improve the high temperature resistance of directionally solidified alloy blade
Oxidation and corrosion and heat resistant energy performance, and the very thin thickness of infiltration layer, to the Effect on Mechanical Properties very little of blade.
Ceramic layer can not only improve the corrosion resistance of blade, blade can also be carried using the heat-insulating property of ceramics
For effective thermal protection；The presence of Co in metal adhesion layer, Cr, Al element can greatly improve the corrosion and heat resistant and antioxygen of blade
Change ability, the presence of metal adhesion layer can strengthen the matching of ceramic layer and blade the matrix thermal coefficient of expansion when being heated, and carry
The life-span of high coating.
Brief description of the drawings
Fig. 1 is the schematic cross-section of the turbine rotor blade of the embodiment of the utility model one.
Fig. 2 is the schematic cross-section of A-A shown in Fig. 1.
Fig. 3 is the schematic diagram of the turbine rotor blade of the embodiment of the utility model one.
Wherein, 1- blades, the anticorrosive coats of 11- first, the anticorrosive coats of 12- second, 13- metal adhesion layers, 14- ceramic layers, 2- every
Seam is split in rib, 3- unit cavitys, 4- tenons, 5- cold air paths, 6- air film holes, 7- coolings.
Embodiment
To make the purpose, technical scheme and advantage of the utility model implementation clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, the technical scheme in the utility model embodiment is further described in more detail.In the accompanying drawings, from beginning
Same or similar element or element with same or like function are represented to same or similar label eventually.Described reality
It is a part of embodiment of the utility model to apply example, rather than whole embodiments.The embodiment described below with reference to accompanying drawing
It is exemplary, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made
Example, belongs to the scope of the utility model protection.Embodiment of the present utility model is described in detail below in conjunction with the accompanying drawings.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of description the utility model and simplifies description, rather than indicate or imply and be signified
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The limitation of novel protected scope.
As shown in Figure 1, Figure 2, Figure 3 shows, a kind of turbine rotor blade, blade 1 is cast using Ni-based directionally solidified superalloy, DS superalloy,
Blade 1 is cavity structure, has the first anticorrosive coat 11 in the inner surface setting of cavity, the outer surface of blade 1 is provided with the second anti-corrosion
Layer 12.Nickel base superalloy has preferable corrosion and heat resistant ability in itself, using directional solidification casting, relative to routine casting side
Formula, not only greatly improved the heat and corrosion resistant ability of blade, and thermal fatigue life, creep rupture strength and creep strength have aobvious
The raising of work.
In the present embodiment, the first anticorrosive coat 11 is the infiltration layer for including aluminium element silicon, and the thickness of infiltration layer is 0.05mm.Blade
1 cavity inner surface forms the infiltration layer of the one very thin element silicon containing aluminium, infiltration layer by way of Al-Si co-infiltrating in blade inner chamber
Formation direction be from inwall towards blade inside, its presence can improve directionally solidified alloy blade resistance to high temperature oxidation and heat resistanceheat resistant it is rotten
Erosion energy performance, and the very thin thickness of infiltration layer, to the Effect on Mechanical Properties very little of blade.It is understood that the thickness of infiltration layer
It can be set according to actual use operating mode, for example, in an alternative embodiment, the thickness of infiltration layer is set to 0.04mm, another
In one alternative, the thickness of infiltration layer is 0.06mm；The thickness of infiltration layer can be any as needed between 0.02~0.1mm
Selection.
In the present embodiment, the second anticorrosive coat 12 sprays the thermal barrier coating of double-decker by way of thermal spraying, including
One metal adhesion layer 13 and a ceramic layer 14, metal adhesion layer 13 are contacted with the outer surface of blade 1, from the appearance of blade 1
Away from the direction spraying of outer surface；Ceramic layer 14 is sprayed on the outside of metal adhesion layer 13.
In the present embodiment, the material of ceramic layer 14 is ZrO2Ceramics, using electro beam physics vapor phase deposition (EB-PVD)
Mode spray, the thickness of ceramic layer 14 is 0.15mm.It is understood that the thickness of ceramic layer 14 can be according to actual use
Operating mode is set, for example, in an alternative embodiment, the thickness of ceramic layer 14 is 0.1m, in another alternative embodiment, ceramics
The thickness of layer 14 is 0.18mm；The thickness of ceramic layer 14 can arbitrarily be set between 0.05~0.25mm as needed.
In the present embodiment, the material of metal adhesion layer 13 is CoCrAlY, and the thickness of metal adhesion layer 13 is 0.1mm.Can
With understanding, the thickness of metal adhesion layer 13 can be set according to actual use operating mode, for example, in an alternative
In, the thickness of metal adhesion layer 13 is 0.08mm, in another alternative embodiment, and the thickness of metal adhesion layer 13 is 0.15mm；
The thickness of metal adhesion layer 13 can arbitrarily be set according to actual use between 0.03~0.2mm.
Ceramic layer 14 can not only improve the corrosion resistance of blade, can also be using the heat-insulating property of ceramics to blade
Effective thermal protection is provided；The presence of Co in metal adhesion layer 13, Cr, Al element can greatly improve blade corrosion and heat resistant and
Oxidation resistance, the presence of metal adhesion layer 13 can strengthen of ceramic layer 14 and blade the matrix thermal coefficient of expansion when being heated
With property, the life-span of coating is improved.
In the present embodiment, the cavity by every rib 2 be divided on multiple unit cavitys 3, tenon 4 be provided with it is multiple cold
Gas passage 5, cold air path 5 is connected with unit cavity 3, for inputting cold air into unit cavity 3.The leading edge of blade 1 is provided with
Multiple air film holes 6, the outer surface of the connection blade 1 of air film hole 6 and unit cavity 3, leading edge is drained to by the cold air in unit cavity 3
Surface, forms cold air film；The trailing edge of blade 1 is provided with multiple coolings and splits seam 7, and cooling splits that seam 7 is used for will be cold in unit cavity 3
Gas is drained to the trailing edge surface.
The utility model additionally provides a kind of engine, and the engine includes turbine rotor blade as described above.Leaf
Piece is cast using Ni-based directionally solidified superalloy, DS superalloy, and nickel base superalloy has preferable corrosion and heat resistant ability in itself, using fixed
To solidified cast, relative to routine casting mode, the heat and corrosion resistant ability of blade, and heat fatigue longevity not only greatly improved
Life, creep rupture strength and creep strength all increase significantly.The outer surface of blade and surface of internal cavity are provided with erosion shield,
The performance and service life of blade are improved, is conducive to improving the performance of engine.
It is last it is to be noted that：Above example is only limited to illustrate the technical solution of the utility model, rather than to it
System.Although the utility model is described in detail with reference to the foregoing embodiments, one of ordinary skill in the art should manage
Solution：It can still be modified to the technical scheme described in foregoing embodiments, or which part technical characteristic is entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from each embodiment of the utility model
The spirit and scope of technical scheme.
Claims (9)
1. a kind of turbine rotor blade, it is characterised in that：
Blade (1) is cast using Ni-based directionally solidified superalloy, DS superalloy, and the blade (1) is cavity structure, in the inner surface of cavity
The first anticorrosive coat (11) is provided with, the outer surface of the blade (1) is provided with the second anticorrosive coat (12).
2. turbine rotor blade as claimed in claim 1, it is characterised in that：First anticorrosive coat (11) is comprising aluminium silicon member
The infiltration layer of element, the thickness of infiltration layer is 0.02~0.1mm.
3. turbine rotor blade as claimed in claim 2, it is characterised in that：Second anticorrosive coat (12) passes through thermal spraying
Mode sprays the thermal barrier coating of double-decker, including a metal adhesion layer (13) and a ceramic layer (14), and the metal glues
The outer surface that layer (13) is connect with the blade (1) is contacted, and the ceramic layer (14) is sprayed on the outer of the metal adhesion layer (13)
Side.
4. turbine rotor blade as claimed in claim 3, it is characterised in that：The material of the ceramic layer (14) is ZrO2Ceramics,
Sprayed by the way of electro beam physics vapor phase deposition.
5. turbine rotor blade as claimed in claim 4, it is characterised in that：The thickness of the ceramic layer (14) be 0.05~
0.25mm。
6. turbine rotor blade as claimed in claim 3, it is characterised in that：The material of the metal adhesion layer (13) is
CoCrAlY, the thickness of the metal adhesion layer (13) is 0.03~0.2mm.
7. the turbine rotor blade as described in any one of claim 1 to 6, it is characterised in that：The cavity passes through every rib (2) point
It is divided on multiple unit cavitys (3), tenon (4) and is provided with multiple cold air paths (5), the cold air path (5) and the unit
Cavity (3) is connected.
8. turbine rotor blade as claimed in claim 7, it is characterised in that：The leading edge of the blade (1) is provided with multiple gas
Fenestra (6), the air film hole (6) connects outer surface and the unit cavity (3) of the blade (1)；The trailing edge of the blade (1) is set
It is equipped with multiple coolings and splits seam (7), seam (7) is split in the cooling is used to the cold air in the unit cavity (3) being drained to the tail
Edge surface.
9. a kind of engine, it is characterised in that：The engine includes turbine rotor blade as claimed in claim 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720084201.3U CN206513407U (en) | 2017-01-23 | 2017-01-23 | A kind of turbine rotor blade and the engine with it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720084201.3U CN206513407U (en) | 2017-01-23 | 2017-01-23 | A kind of turbine rotor blade and the engine with it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206513407U true CN206513407U (en) | 2017-09-22 |
Family
ID=59866846
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720084201.3U Active CN206513407U (en) | 2017-01-23 | 2017-01-23 | A kind of turbine rotor blade and the engine with it |
Country Status (1)
| Country | Link |
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| CN (1) | CN206513407U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113466041A (en) * | 2021-06-29 | 2021-10-01 | 中国航发沈阳发动机研究所 | Turbine blade seepage mechanical property test evaluation method |
| CN114607471A (en) * | 2018-07-19 | 2022-06-10 | 通用电气公司 | Airfoil with adjustable cooling configuration |
-
2017
- 2017-01-23 CN CN201720084201.3U patent/CN206513407U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114607471A (en) * | 2018-07-19 | 2022-06-10 | 通用电气公司 | Airfoil with adjustable cooling configuration |
| CN113466041A (en) * | 2021-06-29 | 2021-10-01 | 中国航发沈阳发动机研究所 | Turbine blade seepage mechanical property test evaluation method |
| CN113466041B (en) * | 2021-06-29 | 2024-01-30 | 中国航发沈阳发动机研究所 | Turbine blade seepage layer mechanical property test evaluation method |
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