CN108119188A - A kind of ceramic matrix composite turbine rotor blade - Google Patents
A kind of ceramic matrix composite turbine rotor blade Download PDFInfo
- Publication number
- CN108119188A CN108119188A CN201711371076.5A CN201711371076A CN108119188A CN 108119188 A CN108119188 A CN 108119188A CN 201711371076 A CN201711371076 A CN 201711371076A CN 108119188 A CN108119188 A CN 108119188A
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- China
- Prior art keywords
- blade
- listrium
- root
- tenon
- obturage
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/284—Selection of ceramic materials
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Ceramic Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Composite Materials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A kind of turbo blade in gas-turbine unit of the present invention, structure are suitable for being manufactured using ceramic matric composite.Integral blade is made of completely ceramic matric composite, including blade, is obturaged listrium, is stretched root and tenon first class sections.Blade stretches root and tongue portion thickness change degree less than common metal blade, and the core precast body formed by silicon carbide fibre braiding is obtained by curing with moulding process.It is relatively thin to obturage listrium structural thickness, is laminated by fiber cloth, and is stretching the listrium transferred at root to root or adjacent different directions are stretched.It is wide at the top and narrow at the bottom in dovetail configuration is fallen to stretch root position, prevents from dropping downwards during installation blade, listrium is obturaged in turbine disk disk edge damage caused by avoiding therefore, and blade key edge carries out fillet processing, prevents sharp corner damage of colliding with from local fiber being caused to damage.The blade construction can provide the functional requirements such as turbo blade is required pneumatically, obturages, assembles, suitable for ceramic matric composite manufacturing process.
Description
Technical field
The present invention relates to a kind of gas turbine engine blade, the turbo blade is answered by composite material especially ceramic base
Condensation material is made, and is mounted on by dove-tail form tenon on rotor disk.Belong to aero-engine or ground and combustion gas wheel peculiar to vessel
Machine.
Background technology
For the turbine rotor blade in aero-engine, the material being currently mainly used is high temperature alloy.High temperature alloy
Higher density makes leaf quality bigger than normal, and the centrifugal force that blade is born is huge, to the turbine disk and relevant connection, support construction
Bearing capacity be proposed very high requirement, aero-turbine components is caused to occupy engine main screw lift very
Large scale.
Have benefited from the development of high-performance ceramic fiber technology of preparing, using the ceramic base composite wood of continuous fiber once tough technology
Material toughness greatly improves, and the mechanical property for having metalloid material shows, and is provided simultaneously with higher temperature resistant capability, good strong
Degree, anti-oxidant, creep-resistant property, are applied in some aero-engine stator parts.
Ceramic matric composite is applied to aircraft engine rotor part, overall performance is promoted and Weight control more has
Effect.But be suitable for the turbine blade arrangement of metal material at present, for example, it is common obturage comb tooth, multiple tooth type tenon, and uncomfortable
Compile in collaboration with precast body preparation and the curing molding of Woven composite.At the same time, the typical structure of these metal blades is needed phase
Position is answered to be machined into net shape, thus can be caused, cutting destroys woven composite internal fiber continuity, structure
Local mechanical loudness is significantly degenerated.
The content of the invention
Therefore, present invention is primarily intended to propose a kind of ceramic matric composite suitable for woven composite technique
Turbine rotor blade structure, the structure can provide the functional requirements such as turbo blade is required pneumatically, obturages, assembles.
By using a kind of improved blade-stretch root-tenon integral structure and using obturaging in the blade construction
Listrium realizes this purpose instead of traditional seal structure such as comb tooth.
To achieve these goals, a kind of ceramic matrix composite turbine rotor blade of the present invention, including blade
(1), obturage listrium, stretch root (7) and tenon (9)；
The blade (1) is by blade tip (12), blade root (13), leaf basin surface (1b), blade back surface (1a) and blade inlet edge
(1c) is formed；The cross section aerofoil profile of blade (1) possesses curved air mechanics contour；The air mechanics contour is from blade root
(13) blade tip (12) is extended longitudinally to along blade；The air mechanics contour has variable vane thickness, according to weaver
Skill feature, vane thickness are recommended in 2-5mm；The air mechanics contour is by leaf basin surface (1b) and blade back surface (1a) structure
Into；The leaf basin surface (1b) and blade back surface (1a) surround entire blade by blade inlet edge (1c) and blade trailing edge (1d).
The listrium of obturaging is including obturaging listrium (5), ladder transition envelope between obturaging listrium (2) in stage, turning stator grade
Listrium (6) is obturaged in tight listrium (4) and end face；According to obturage requirement choose and obturage listrium form with the use of above-mentioned four class；Institute
State and listrium (2) obturaged in stage, turn stator grade between obturage listrium (5), ladder transition obturages listrium (4) and listrium is obturaged in end face
(6) it is arranged at blade root, is separately designed in grade at blade root in flake, between grade, interior intersection and the tenon end between grade of grade
Face.The listrium of obturaging is laminated by control of two-dimensional braided fiber cloth, by the way that braiding layer number is controlled to control listrium thickness.
Listrium (2) is obturaged in grade to avoid directly into the turbine disk for blockading combustion gas in runner；Listrium (5) use is obturaged between grade
In blockading the combustion gas between stators and rotor；Ladder transition obturages the ladder knot of listrium (4) cooperation stators corresponding position
Structure (not shown) obturages effect between grade for improving；It obturages listrium (6) and passes through adjacent leaf for combustion gas between barrier level again in end face
Gap enters the turbine disk between piece stretches root.
Obturage listrium and both transferred at root (7) to stretching stretching at root (7), at the same also to adjacent different directions listrium turnover with
Extension (obturages listrium (2) and ladder transition obturages listrium (4), ladder transition obturages listrium (4) and turns between stator grade in stage
Obturage listrium (5), turn stator grade between obturage listrium (5) with listrium (6) is obturaged in end face, ladder transition obturages listrium (4) and end face
Obturage listrium (6)), to obturage listrium (2) in the stage of each position different directions, to turn to obturage listrium between stator grade
(5), ladder transition obturages listrium (4) and end face obturages listrium (6) and interfixes, and with blade (1)-stretch root (7)-tenon (9)
Integral structure more closely combines.
Structure and layered relationship of the listrium intersection according to turnover are obturaged, obturages listrium and blade (1)-stretch root (7)-tenon
(9) structure need to be finally closely joined together by multiple curing process.
The each turning point for obturaging listrium is all designed with certain fillet, avoids ceramic fibre local damage caused by acutely transferring
Wound and performance degradation.
The listrium of obturaging is primarily subjected to runner Pneumatic pressure, heat and oscillating load, and thickness too thin (should not easily vibrate
Problem), also should not too thick (itself centrifugal force is big, is easily broken in the turning point with stretching root), recommend thickness in 2-3mm.
It is described stretch root (7) in it is wide at the top and narrow at the bottom fall dovetail configuration, stretch root (7) be located at obturage below listrium, blade (1) and tenon
(9) between.Root inclined-plane (3) is stretched to contact with the corresponding surface of tongue-and-groove (14)；Two opposed facets angles of root (7) are stretched about 15 °；
The tenon (9) is dove-tail form tenon, the working face lower edge (10) of tenon (9) and tenon root (8) turning point
Equipped with fillet, prevent that foreign object is damaged caused by tenon root (8) deflection angle during installing and using.Rabbet working face (15) is attached
Nearly fiber is sprawled along working face, is suitble to bear the extrusion stress perpendicular to working face；Described two working face angle (dovetails of tenon
Angle) at 60-80 °；Rabbet working face (15) is contacted with the corresponding surface of tongue-and-groove (16)；Tenon lateral cross section may be either that rectangle is alternatively
Parallelogram.Rabbet working face (15) outermost surface recommends high-temperature wear resistant coating, at this coating can with blade other
Position is different.
The blade (1) stretches the scope of root (7) and the control of tenon (9) thickness change degree needs in weaving permission
Interior, the ratio between tenon the widest part and blade thinnest part thickness are recommended in the range of 6-12 times.
The blade (1) stretches root (7) and tenon (9) by the core precast body that fibrage forms by filling matrix, causes
Densification is molded to obtain, and ensures the continuity of inside configuration fiber.
The blade will be represented with stretching root and tongue portion being integrally formed structure with " blade-stretch root-tenon ".
Blade recommends ceramic matric composite and is made, it is preferable that enhancing mutually selects SiC continuous fibers, and matrix is chosen
SiC。
The composite material includes the use of bundle weave and the composite material parts formed using matrix filling densification.
Advantages of the present invention and effect are：Blade of the present invention possesses dove-tail form tenon, stretches root position dovetail configuration, thin
Type obturages listrium, and this structure has many advantages for woven composite.
For manufacture, blade-stretch root-tenon integral structure is suitble to using 2.5 dimensions or three dimensional weaving technique, and cooperation increases
Reducing-yarn technique integral weaving and integrally densification shaping；Listrium is obturaged to be suitble to be laminated and pass through using control of two-dimensional braided fiber cloth
Root is stretched stretching to turn at root, cures to combine closely with blade-stretch root-tenon integral structure again.
For this blade strength, the preparation process of blade-stretch root-tenon integral structure can make fiber in structure
The continuity in portion keeps good, and overall structure bearing capacity will not be significantly affected because local fiber is cut off.Blade-stretch
The fiber principal direction of root-tenon structure is substantially along blade longitudinal direction, and (turbo blade is most main for the centrifugal force for being suitble to bear along blade longitudinal direction
Want one of load)；Nearby fiber is sprawled along working face in rabbet working face, is suitble to bear the extrusion stress perpendicular to working face；Envelope
Root-tenon integral structure load is relatively low compared with blade-stretch for tight listrium, is suitble to using relatively thin control of two-dimensional braided lamination process
Control structure weight.Integral turbine blade is made of composite material of the same race, there is no between each structure division due to material properties
The thermal dilation difference and thermal stress that difference generates.
Description of the drawings
Fig. 1 is turbo blade blade back side look down on the rendering.
Fig. 2 looks up design sketch for turbo blade leaf basin side.
After Fig. 3 is packed into tongue-and-groove for turbo blade leaf, tenon position sectional view during axial locking plate is not installed.
After Fig. 4 is loaded completely for turbo blade leaf, tenon position sectional view under working condition.
Specific embodiment
The present invention is applied to gas-turbine unit rotor blade, and blade construction matches composite material preparation process, and
It is specifically adapted for low-pressure turbine blade.Fig. 1-Fig. 4 gives a low-pressure turbine blade structure case.
With reference to known structure type, shown blade (11) includes blade (1), obturages listrium, stretches root in fig. 1 and 2
(7) and tenon (9) part；The listrium of obturaging is located at blade root (13) position；It is described stretch root (7) be located at obturage under listrium
Between side, blade (1) and tenon (9).
The cross section aerofoil profile of blade (1) possesses curved air mechanics contour, and the air mechanics contour is from blade root
(13) blade tip (12) is extended longitudinally to along blade；This profile has variable vane thickness, by leaf basin surface (1b) and blade back
Surface (1a) is formed；The leaf basin surface (1b) and blade back surface (1a) are surrounded by blade inlet edge (1c) and blade trailing edge (1d)
Entire blade.
The blade construction case that Fig. 1-Fig. 4 is provided is mounted on using dove-tail form tenon and is provided in the wheel disc of dove-tail form tongue-and-groove,
Recommend at 60-90 ° at dovetail angle.
Particularly, described root (7) position of stretching is wide at the top and narrow at the bottom in dovetail configuration, and two opposed facets angles are recommended at 15 °
Up and down, not install axial locking plate when preventing installation blade, turbine disk disk edge touches caused by blade drops downwards
It hits blade and obturages listrium, see Fig. 3.When blade is not installed completely, stretch root inclined-plane (3) and contacted with the corresponding surface of tongue-and-groove (14)；Blade
Under being loaded completely or being in running order, figure (4) is seen, rabbet working face (15) are contacted with the corresponding surface of tongue-and-groove (16).
Blade (11) is made of composite material, preferably recommends Continuous Fiber Reinforced Ceramic Matrix Composites, passes through
Two dimension, 3 D weaving manufacture precast body are simultaneously obtained by repeatedly densification shaping.
Particularly, the blade (1)-stretch root (7)-tenon (9) coordinates certain increase using 2.5 dimensions or three dimensional weaving technique
Reducing-yarn technique integral weaving and integrally densification shaping obtain.
Blade (1)-stretch the thickness change degree of root (7)-tenon (9) part, it is necessary to according to braiding increase and decrease yarn process control
In allowed limits.Blade can select it is axially mounted parallel to wheel disc, also may be selected it is axially in a certain angle with wheel disc, i.e.,
Tenon lateral cross section may be either that rectangle is alternatively parallelogram.
The blade (1)-stretch root (7)-tenon (9) when using 2.5 dimension weaving, will improve warp thread and (be indulged along blade
To) ratio；When using 3 D weaving technique, low braiding angle is used；It is suitble to bear the centrifugal force (whirlpool along blade longitudinal direction with this
One of main load of impeller blade).Tenon (9) working face nearby fiber needs sprawled along working face, approximation make fiber laterally by
Compression, is suitble to bear the extrusion stress perpendicular to working face with this.
Tenon root (8) structure needs to keep certain height longitudinally, i.e., the working face lower edge (10) of tenon (9) and
Tenon root (8) bottom surface fore-and-aft distance is enough, disperses shear stress of the tenon root along end face to provide enough structure spaces
With compression stress.
The blade (1)-stretch root (7)-tenon (9) is equipped with fillet at the transition variation of type face, makes fiber smooth transition,
Reduce damage.Particularly, the working face lower edge (10) of tenon (9) and tenon root turning point also are provided with fillet, prevent from installing
Foreign object is damaged caused by tenon root (8) structure deflection angle during use.
The listrium of obturaging includes obturaging listrium (2) in stage, turns to obturage listrium (5), ladder transition envelope between stator grade
Tight listrium (4), listrium (6) is obturaged in end face；It is located at respectively in grade at blade root, between grade, interior intersection, the tenon end face between grade of grade.
Listrium (2) is obturaged in grade and is avoided for blockading combustion gas in runner directly into the turbine disk, listrium (5) is obturaged for blockading whirlpool between grade
The combustion gas between stator and rotor is taken turns, the hierarchic structure that ladder transition obturages listrium (4) cooperation stators corresponding position (is not shown
Go out) effect is obturaged between grade for improving, end face obturage listrium (6) for combustion gas between barrier level again by adjacent blades stretch root it
Between gap enter the turbine disk.Listrium structure is obturaged with the use of this four class according to the demand of obturaging.
The listrium of obturaging is laminated using control of two-dimensional braided fiber cloth, and thickness is determined according to aerodynamic loading and material property
With weaving the number of plies.It obturages listrium and was both transferred at root (7) to stretching stretching at root (7), while also turn to the listrium of adjacent different directions
Folding (obturages listrium (2) and ladder transition obturages listrium (4), ladder transition obturages listrium (4) and turns stator with extension in stage
Obturage listrium (5) between grade, turn stator grade between obturage listrium (5) and end face obturage listrium (6), ladder transition obturage listrium (4) with
Obturage listrium (6) in end face), to obturage listrium (2) in the stage of each position different directions, to turn to obturage edge between stator grade
Plate (5), ladder transition obturage listrium (4) and end face obturages listrium (6) and interfixes, and with blade (1)-stretch root (7)-tenon
(9) integral structure more closely combines.
Structure and layered relationship of the listrium intersection according to turnover are obturaged, obturages listrium and blade (1)-stretch root (7)-tenon
(9) structure need to be finally closely joined together by multiple curing process.
Shown in Fig. 1-Fig. 2, each turning point for obturaging listrium is all designed with certain fillet, and ceramic fibre is avoided acutely to transfer
Caused local damage and performance degradation.
The listrium of obturaging is primarily subjected to runner Pneumatic pressure, heat and oscillating load, and thickness too thin (should not easily vibrate
Problem), also should not too thick (itself centrifugal force is big, is easily broken in the turning point with stretching root), recommend thickness in 2-3mm.
Integral blade (11) recommends third generation hypoxemia and free carbon content silicon carbide fibre, to obtain preferable height
Enduring quality under warm combustion gas environment.
Integral blade surface need to prepare Environmental Barrier Coatings on Si-based Ceramics, prevent the compositions such as high-temperature fuel gas and material internal residual free carbon
Chemical reaction, causes material property degradation.
Particularly, blade tenon working face (15) outermost surface recommends high-temperature wear resistant coating, and coating can be at this
Other positions of blade are different.
Shown in Fig. 3-Fig. 4, metal worm disk tenon groove structure is substantially complementary with tenon structure, but there was only piece tenon under working condition
Gap is left at head working face (15) and blade contact, other positions, to coordinate the thermal expansion of blade and turbine disk mismatch, leaf
The gap of piece tenon bottom surface and turbine disc mortise bottom surface is used to fix blade axial locking mechanism (not shown).
Claims (10)
1. a kind of ceramic matrix composite turbine rotor blade, it is characterised in that：Including blade (1), obturage listrium, stretch root (7)
With tenon (9)；
The blade (1) is by blade tip (12), blade root (13), leaf basin surface (1b), blade back surface (1a) and blade inlet edge (1c) structure
Into；The cross section aerofoil profile of blade (1) possesses curved air mechanics contour；The leaf basin surface (1b) and blade back surface (1a)
Entire blade is surrounded by blade inlet edge (1c) and blade trailing edge (1d)；
It is described obturage listrium include stage in obturage listrium (2), turn stator grade between obturage listrium (5), ladder transition obturages edge
Listrium (6) is obturaged in plate (4) and end face；Listrium (2) is obturaged in the stage, turn stator grade between obturage listrium (5), ladder transition
It obturages listrium (4) and end face is obturaged listrium (6) and is arranged in flake at blade root, separately design in grade at blade root, between grade,
Interior intersection and the tenon end face between grade of grade；
It obturages listrium and was both transferred at root (7) to stretching stretching at root (7), while also transfer to the listrium of adjacent different directions with prolonging
It stretches, to obturage listrium (2) in the stage of each position different directions, to turn to obturage listrium (5), ladder transition between stator grade
It obturages listrium (4) and end face obturages listrium (6) and interfixes；
The listrium of obturaging bears runner Pneumatic pressure, heat and oscillating load, and thickness is in 2-3mm；
It is described stretch root (7) in it is wide at the top and narrow at the bottom fall dovetail configuration, stretch root (7) be located at obturage below listrium, blade (1) and tenon (9)
Between；Root inclined-plane (3) is stretched to contact with the corresponding surface of tongue-and-groove (14)；
The tenon (9) is dove-tail form tenon, and the working face lower edge (10) of tenon (9) and tenon root (8) turning point are equipped with
Fillet prevents that foreign object is damaged caused by tenon root (8) deflection angle during installing and using；Rabbet working face (15) is fine nearby
Dimension is sprawled along working face, bears the extrusion stress perpendicular to working face；Rabbet working face (15) surface (16) corresponding with tongue-and-groove connects
It touches；
The blade will be represented with stretching root and tenon being integrally formed structure with blade-stretch root-tenon.
2. a kind of ceramic matrix composite turbine rotor blade according to claim 1, it is characterised in that：The air moves
Mechanics profile is made of leaf basin surface (1b) and blade back surface (1a)；Air mechanics contour longitudinally prolongs from blade root (13) along blade
Extend blade tip (12)；Air mechanics contour has variable vane thickness, and vane thickness is in 2-5mm.
3. a kind of ceramic matrix composite turbine rotor blade according to claim 1, it is characterised in that：Envelope in the grade
Tight listrium (2) is avoided for blockading combustion gas in runner directly into the turbine disk；Listrium (5) is obturaged between grade for blockading stators
Combustion gas between rotor；Ladder transition obturages the hierarchic structure of listrium (4) cooperation stators corresponding position for improving between grade
Obturage effect；End face obturage listrium (6) for combustion gas between barrier level again by adjacent blades stretch root between gap enter turbine
Disk.
4. a kind of ceramic matrix composite turbine rotor blade according to claim 1, it is characterised in that：It is described to obturage edge
Plate is laminated by control of two-dimensional braided fiber cloth, by the way that braiding layer number is controlled to control listrium thickness；Obturage each turning point of listrium
All be designed with fillet, avoid ceramic fibre acutely transfer caused by local damage and performance degradation.
5. a kind of ceramic matrix composite turbine rotor blade according to claim 1, it is characterised in that：The tight listrium
For intersection according to the structure and layered relationship of turnover, multiple curing process need to be passed through by obturaging listrium and blade-stretch root-tenon structure
Finally it is closely joined together.
6. a kind of ceramic matrix composite turbine rotor blade according to claim 1, it is characterised in that：The blade
(1), stretching root (7) and tenon (9) thickness change degree needs to control in the range of weaving permission, tenon the widest part and leaf
The ratio between body thinnest part thickness is in the range of 6-12 times.
7. a kind of ceramic matrix composite turbine rotor blade according to claim 1, it is characterised in that：It is described to stretch root
(7) two opposed facets angles are about 15 °；Described two working face angles of tenon are at 60-80 °.
8. a kind of ceramic matrix composite turbine rotor blade according to claim 1, it is characterised in that：Tenon transverse cutting
Face is rectangle or is parallelogram；Rabbet working face (15) outermost surface uses high-temperature wear resistant coating.
9. a kind of ceramic matrix composite turbine rotor blade according to claim 1, it is characterised in that：The blade
(1), root (7) and tenon (9) are stretched by the core precast body that fibrage forms by filling matrix, and densification shaping is obtained, protected
Demonstrate,prove the continuity of inside configuration fiber.
10. a kind of ceramic matrix composite turbine rotor blade according to claim 9, it is characterised in that：Fibrous material
For SiC.
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| CN201711371076.5A CN108119188B (en) | 2017-12-19 | 2017-12-19 | Ceramic matrix composite turbine rotor blade |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108897931A (en) * | 2018-06-14 | 2018-11-27 | 南京航空航天大学 | A kind of design method of ceramic base turbine rotor blade precast body |
| CN111102014A (en) * | 2019-12-04 | 2020-05-05 | 南京航空航天大学 | Ceramic matrix composite turbine integral blade disc structure and preparation method thereof |
| CN111365079A (en) * | 2020-04-01 | 2020-07-03 | 南京航空航天大学 | Ceramic matrix composite turbine rotor blade disk tenon connecting structure and turbine disk |
| CN112145237A (en) * | 2020-09-09 | 2020-12-29 | 兰州长城机械工程有限公司 | Long-handle moving blade suitable for high-temperature flue gas turbine |
| CN113107605A (en) * | 2021-05-06 | 2021-07-13 | 南京航空航天大学 | Ceramic matrix composite double-T-shaped turbine rotor blade structure |
| CN113217112A (en) * | 2021-06-21 | 2021-08-06 | 北京航空航天大学 | Manufacturing method of titanium alloy hollow blade and titanium alloy hollow blade |
| CN113236583A (en) * | 2021-03-19 | 2021-08-10 | 北京航空航天大学 | Design method for arc tenon blade root extending structure |
| CN113756879A (en) * | 2021-09-08 | 2021-12-07 | 江苏江航智飞机发动机部件研究院有限公司 | Turbine blade of aircraft engine |
| CN116906126A (en) * | 2023-09-14 | 2023-10-20 | 中国航发北京航空材料研究院 | Multi-body guide vane of ceramic matrix composite and single crystal superalloy and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108897931A (en) * | 2018-06-14 | 2018-11-27 | 南京航空航天大学 | A kind of design method of ceramic base turbine rotor blade precast body |
| CN108897931B (en) * | 2018-06-14 | 2022-03-25 | 南京航空航天大学 | Design method of ceramic-based turbine rotor blade preform |
| CN111102014A (en) * | 2019-12-04 | 2020-05-05 | 南京航空航天大学 | Ceramic matrix composite turbine integral blade disc structure and preparation method thereof |
| CN111365079A (en) * | 2020-04-01 | 2020-07-03 | 南京航空航天大学 | Ceramic matrix composite turbine rotor blade disk tenon connecting structure and turbine disk |
| CN112145237A (en) * | 2020-09-09 | 2020-12-29 | 兰州长城机械工程有限公司 | Long-handle moving blade suitable for high-temperature flue gas turbine |
| CN113236583A (en) * | 2021-03-19 | 2021-08-10 | 北京航空航天大学 | Design method for arc tenon blade root extending structure |
| CN113107605A (en) * | 2021-05-06 | 2021-07-13 | 南京航空航天大学 | Ceramic matrix composite double-T-shaped turbine rotor blade structure |
| CN113217112A (en) * | 2021-06-21 | 2021-08-06 | 北京航空航天大学 | Manufacturing method of titanium alloy hollow blade and titanium alloy hollow blade |
| CN113756879A (en) * | 2021-09-08 | 2021-12-07 | 江苏江航智飞机发动机部件研究院有限公司 | Turbine blade of aircraft engine |
| CN116906126A (en) * | 2023-09-14 | 2023-10-20 | 中国航发北京航空材料研究院 | Multi-body guide vane of ceramic matrix composite and single crystal superalloy and preparation method thereof |
| CN116906126B (en) * | 2023-09-14 | 2023-12-08 | 中国航发北京航空材料研究院 | Multi-body guide vane of ceramic matrix composite and single crystal superalloy and preparation method thereof |
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