CN112576314A - High-temperature-resistant turbine disc based on ceramic material - Google Patents
High-temperature-resistant turbine disc based on ceramic material Download PDFInfo
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- CN112576314A CN112576314A CN202011631858.XA CN202011631858A CN112576314A CN 112576314 A CN112576314 A CN 112576314A CN 202011631858 A CN202011631858 A CN 202011631858A CN 112576314 A CN112576314 A CN 112576314A
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- Prior art keywords
- ceramic
- disc
- turbine
- temperature
- disk
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- 229910010293 ceramic material Inorganic materials 0.000 title claims abstract description 29
- 239000000919 ceramic Substances 0.000 claims abstract description 86
- 239000002184 metal Substances 0.000 claims abstract description 24
- 238000000576 coating method Methods 0.000 claims abstract description 14
- 239000011248 coating agent Substances 0.000 claims description 13
- 239000007769 metal material Substances 0.000 claims description 8
- 230000005540 biological transmission Effects 0.000 claims description 6
- 239000000463 material Substances 0.000 abstract description 10
- 238000007790 scraping Methods 0.000 abstract description 6
- 238000010008 shearing Methods 0.000 abstract description 3
- 230000002708 enhancing effect Effects 0.000 abstract description 2
- 241000264877 Hippospongia communis Species 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 241001391944 Commicarpus scandens Species 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Images
Classifications
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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
- F01D5/02—Blade-carrying members, e.g. rotors
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
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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
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a high-temperature-resistant turbine disc based on a ceramic material, which comprises a turbine main body, wherein the turbine main body comprises a ceramic disc and ceramic blades, the ceramic disc and the ceramic blades are made of the same or different high-temperature-resistant ceramic materials, a front counterweight sheet is arranged at the position of a central disc shaft of the ceramic disc and used for dynamic balance and balancing of the turbine main body, the front counterweight sheet is bonded at the position of the central disc shaft of the ceramic disc through a bonding metal sheet, the front counterweight sheet is positioned at the same side with the airflow incoming flow direction, and the blade tips of the ceramic blades are provided with blade tip easy-to-grind coatings. According to the invention, a plurality of unique structures are designed according to the characteristics of the ceramic material, so that the ceramic material has the advantages of facilitating dynamic balance material removal, enhancing the anti-shearing capability, avoiding blade tip scraping and the like, and the reliability and the safety of the assembly and the operation of the ceramic-based turbine disk are improved.
Description
Technical Field
The invention relates to a high-temperature-resistant turbine disc based on a ceramic material, and belongs to the structural design direction of an engine turbine disc in the technical field of aviation.
Background
The improvement of the turbine front temperature of the aircraft engine is a continuous pursuit of designers, the overall performance of the engine can be greatly improved by the higher turbine front temperature, and the temperature resistance requirement on turbine blade materials is also improved accordingly. In order for engine turbine blades to be able to withstand higher and higher temperatures, conventional metallic materials have not been able to meet the demand, and the use of ceramic-based materials will be a necessary trend for turbine blades. In recent years, the machining and forming technology of ceramic materials is more and more mature, and the adoption of ceramic-based materials to manufacture turbine disks will become one of the mainstream designs of high-temperature-resistant turbine disks in the future.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide a high-temperature-resistant turbine disc design based on a ceramic material, a plurality of unique structures are designed according to the characteristics of the ceramic material, the high-temperature-resistant turbine disc has the advantages of facilitating dynamic balance material removal, enhancing the anti-shearing capability, avoiding blade tip scraping and the like, and the reliability and the safety of the assembly and the operation of the ceramic-based turbine disc are improved.
The invention is realized by the following technical scheme.
The utility model provides a high temperature resistant turbine dish based on ceramic material, includes turbine main part, turbine main part includes ceramic dish, ceramic blade, ceramic dish and ceramic blade are made by the same or different high temperature resistant ceramic material, the central disk axle position of ceramic dish is provided with preceding balance weight piece for the dynamic balance trim of turbine main part, preceding balance weight piece is bonded through the bonding sheetmetal and is in the central disk axle position of ceramic dish, preceding balance weight piece and air current incoming flow direction homonymy, the apex of ceramic blade is provided with the easy wear coating of apex.
Preferably, the bonding metal sheet is made of a soft metal material. The binding metal sheet is used in cooperation with the front weight plate, is arranged between the front weight plate and the ceramic disk to bind the front weight plate and the ceramic disk, and has the same torque transmission structure as the ceramic disk.
Preferably, the thickness of the bonding metal sheet is not more than 0.4 mm.
Preferably, the blade tip abradable coating is made of an abradable metal material.
Preferably, the ceramic disc is an equal-thickness disc or an equal-strength disc, and the two surfaces of the central disc shaft of the ceramic disc are provided with fine grooves which are in a shape of a spider-web fine groove, a honeycomb shape or a fishnet shape.
Preferably, the groove width and the groove depth are not more than 0.3 mm.
Preferably, the front weight plate is provided with a torque transmission structure identical to that of the ceramic disc.
Preferably, the ceramic disc further comprises a rear weight plate, the front weight plate and the rear weight plate are respectively located on two sides of the ceramic disc, and the rear weight plate is bonded to the central disc shaft of the ceramic disc through a bonding metal sheet. The front counterweight plate and the rear counterweight plate are convenient for the turbine disc to perform dynamic balance on one hand, and on the other hand, the ceramic disc is prevented from being in direct contact with the rotating shaft, so that the assembly precision is improved
Preferably, the inner hole diameter of the front weight plate is the same as that of the ceramic disc, and the ratio of the outer diameter d to the hub radius H of the ceramic disc is not more than 0.6.
Preferably, the inner hole diameter of the rear weight plate is the same as that of the ceramic disc, and the ratio of the outer diameter d to the hub radius H of the ceramic disc is not more than 0.6.
Preferably, the front weight plate and the rear weight plate are made of alloy materials.
Preferably, the geometry of the tip abradable coating is the natural extension of the tip profile of the ceramic blade. When the ceramic disk is operated at high speed, the blade tip abradable coating is worn away by scraping with the casing, and the thickness will eventually decrease until it no longer scrapes with the casing.
When the front counterweight sheet and the rear counterweight sheet are assembled with the turbine disc, the front counterweight sheet and the rear counterweight sheet are pressed and assembled with the bonding metal sheet in a hot state, the bonding metal sheet is soft in the hot state, and partial materials of the bonding metal sheet are pressed into the fine grooves.
Compared with the prior art, the invention has the advantages that:
first, the problem that the ceramic disk is too brittle to be material balanced is solved. The ceramic material has the characteristics of brittle performance and nonuniform performance, the pure ceramic disc has large dynamic unbalance after being processed, and the rotor dynamic balance design is carried out by controlling the material removal amount once the pure ceramic disc is formed. Through arranging the balance weight plate, the possibility of de-balancing is provided for the ceramic-based turbine disc, and the problem of the dynamic balance design of the ceramic disc is solved.
Secondly, the problem of bonding of the metal material and the ceramic material is solved. The surface of the ceramic material is brittle and is easy to peel off when being impacted. By the hot press mounting method, the balance weight sheet and the ceramic disc are tightly bonded into a whole by the bonding metal sheet and pressed into the spider-web thin groove, so that on one hand, the shearing resistance of the bonding surface is improved, and on the other hand, the balance weight sheet is also used as a buffer material between the shaft and the ceramic disc, and the damage and the peeling of the ceramic are avoided.
Thirdly, the problem of scraping and breaking of the ceramic blade and the casing is solved. The ceramic material is hard and brittle, and the blade is subjected to a large tangential load if the blade is scratched with the casing, so that the blade is easy to break at the blade root. By arranging the blade tip easily-abraded coating, the blade tip is automatically abraded from the blade tip when in scraping, so that the ceramic blade is prevented from being damaged, and meanwhile, the blade tip gap can be ensured to be the minimum value.
Drawings
FIG. 1 is a front perspective view of the present invention;
FIG. 2 is a rear perspective view of the present invention;
FIG. 3 is a front and side view of the present invention;
in the figure: 1. the ceramic blade comprises a ceramic disc, 2, ceramic blades, 3, a front counterweight sheet, 4, a bonding metal sheet, 5, a blade tip easily-ground coating, 6, a fine groove, 7 and a rear counterweight sheet;
the front weight plate and the bonding metal plate are subjected to explosion treatment in fig. 1, and the rear weight plate and the bonding metal plate are subjected to explosion treatment in fig. 2.
Detailed Description
The invention is further described with reference to the following drawings and specific examples, which are not intended to be limiting.
As shown in fig. 1 to 3, a high temperature resistant turbine disc based on a ceramic material includes a turbine main body, the turbine main body includes a ceramic disc 1 and a ceramic blade 2, the ceramic disc 1 and the ceramic blade 2 are made of the same or different high temperature resistant ceramic materials, a front weight plate 3 is disposed at a central disc axis position of the ceramic disc 1 for dynamic balance and balancing of the turbine main body, the front weight plate 3 is bonded at the central disc axis position of the ceramic disc 1 through a bonding metal sheet 4, the front weight plate 3 is disposed at the same side as an airflow incoming flow direction, and a blade tip abradable coating 5 is disposed at a blade tip of the ceramic blade 2.
As a preferred embodiment, the bonding metal sheet 4 is made of a soft metal material. The bonding metal sheet 4 is used in cooperation with the front weight 3, is disposed between the front weight 3 and the ceramic disk 1 to bond the front weight 3 and the ceramic disk 1, and has the same torque transmission structure as the ceramic disk 1.
In a preferred embodiment, the thickness of the bonding metal sheet 4 is not greater than 0.4mm, and 0.4mm is selected in this embodiment.
As a preferred embodiment, the tip abradable coating 5 is made of an abradable metal material.
In a preferred embodiment, the ceramic disk 1 is an equal-thickness disk or an equal-strength disk, and the ceramic disk has fine grooves 6 on both sides of the central disk axis, wherein the fine grooves 6 are in the shape of spider-web fine grooves, honeycombs or fishmeshes.
As a preferable embodiment, the groove width and the groove depth are not more than 0.3mm, and 0.3mm is selected in the embodiment.
As a preferred embodiment, the front weight plate 3 is provided with the same torque transmission structure as the ceramic disc 1.
As a preferred embodiment, the ceramic disc further comprises a rear weight plate 7, the front weight plate 3 and the rear weight plate 7 are respectively located at two sides of the ceramic disc 1, the rear weight plate 7 is bonded at the central disc axis position of the ceramic disc 1 through a bonding metal sheet 4, and the rear weight plate 7 is not arranged in the same torque transmission structure of the ceramic disc 1. Preceding counter weight piece 3 and back counter weight piece 7 are convenient for the turbine dish on the one hand and are done dynamic balance, and on the other hand avoids ceramic dish and pivot direct contact, improves the effect of assembly precision.
In a preferred embodiment, the inner diameter of the front weight plate 3 is the same as that of the ceramic disc 1, and the ratio of the outer diameter d to the hub radius H of the ceramic disc 1 is not more than 0.6, and 0.4 is selected in this embodiment.
In a preferred embodiment, the inner diameter of the rear weight plate 7 is the same as that of the ceramic disc 1, and the ratio of the outer diameter d to the hub radius H of the ceramic disc 1 is not more than 0.6, and 0.4 is selected in this embodiment.
As a preferred embodiment, the front weight plate 3 and the rear weight plate 7 are made of an alloy material.
As a preferred embodiment, the geometry of the tip abradable coating 5 is a natural extension of the tip profile of the ceramic blade 2. When the ceramic disk 1 is operated at high speed rotation, the tip abradable coating 5 is worn away by scraping against the casing, and the thickness will eventually decrease until it no longer scrapes against the casing.
When the front counterweight plate 3 and the rear counterweight plate 7 are assembled with the turbine disc 1, the front counterweight plate and the rear counterweight plate are pressed together with the bonding metal sheet 4 in a hot state, the bonding metal sheet 4 is soft in the hot state, and part of materials of the bonding metal sheet are pressed into the thin grooves.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention.
Claims (10)
1. The high-temperature-resistant turbine disc based on the ceramic materials is characterized by comprising a turbine main body, wherein the turbine main body comprises a ceramic disc (1) and ceramic blades (2), the ceramic disc (1) and the ceramic blades (2) are made of the same or different high-temperature-resistant ceramic materials, a front counterweight sheet (3) is arranged at the position of a central disc shaft of the ceramic disc (1) and used for dynamic balance balancing and balancing of the turbine main body, the front counterweight sheet (3) is bonded at the position of the central disc shaft of the ceramic disc (1) through a bonding metal sheet (4), the front counterweight sheet (3) is arranged on the same side with the air flow incoming direction, and a blade tip of each ceramic blade (2) is provided with a blade tip easy-to-grind coating (5).
2. The ceramic material-based high-temperature-resistant turbine disc as claimed in claim 1, characterized in that the bonding metal sheet (4) is made of a soft metal material.
3. The ceramic material-based high-temperature-resistant turbine disc as claimed in claim 1, characterized in that the thickness of the bonding metal sheet (4) is not more than 0.4 mm.
4. The ceramic material-based high temperature-resistant turbine disc as claimed in claim 1, characterized in that the tip abradable coating (5) is made of an abradable metal material.
5. The ceramic material-based high-temperature-resistant turbine disk according to claim 1, wherein the ceramic disk (1) is an equal-thickness disk or an equal-strength disk, the ceramic disk has fine grooves (6) on both sides of a central disk shaft, and the fine grooves (6) are in the shape of a spider-web fine groove, a honeycomb or a fish-web.
6. The ceramic material-based high temperature-resistant turbine disc as claimed in claim 5, wherein the groove width and the groove depth are not greater than 0.3 mm.
7. High temperature resistant turbine disc based on ceramic material according to claim 1, characterized in that the front weight stack (3) is provided with the same torque transmission structure as the ceramic disc (1).
8. The ceramic material-based high-temperature-resistant turbine disc as claimed in claim 1, further comprising a rear weight plate (7), wherein the front weight plate (3) and the rear weight plate (7) are respectively located on both sides of the ceramic disc (1), and the rear weight plate (7) is bonded to the central disc axis position of the ceramic disc (1) through a bonding metal sheet (4).
9. The refractory turbine disk based on ceramic material according to any of claims 1 to 8, characterized in that the inner hole diameter of the front weight plate (3) is the same as that of the ceramic disk (1), and the ratio of the outer diameter d to the hub radius H of the ceramic disk (1) is not more than 0.6.
10. The refractory turbine disc based on ceramic material according to any one of claims 1 to 8, characterized in that the geometry of the tip abradable coating (5) is a natural extension of the tip profile of the ceramic blade (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011631858.XA CN112576314A (en) | 2020-12-31 | 2020-12-31 | High-temperature-resistant turbine disc based on ceramic material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011631858.XA CN112576314A (en) | 2020-12-31 | 2020-12-31 | High-temperature-resistant turbine disc based on ceramic material |
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| Publication Number | Publication Date |
|---|---|
| CN112576314A true CN112576314A (en) | 2021-03-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011631858.XA Pending CN112576314A (en) | 2020-12-31 | 2020-12-31 | High-temperature-resistant turbine disc based on ceramic material |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4362775A (en) * | 1979-07-05 | 1982-12-07 | Toray Industries, Inc. | Polyester film-heat-bonded metal sheet and container made thereof |
| CN101125753A (en) * | 2006-06-08 | 2008-02-20 | 苏舍美特科（美国）公司 | Dysprosia stabilized zirconia abradable |
| CN104769228A (en) * | 2012-11-06 | 2015-07-08 | 西门子能量股份有限公司 | Turbine airfoil abradable coating system and corresponding turbine blades |
| CN105452530A (en) * | 2013-08-08 | 2016-03-30 | 索拉透平公司 | High porosity abradable coating |
| CN106968716A (en) * | 2016-11-21 | 2017-07-21 | 北京航空航天大学 | Ceramic matric composite turbine blisks |
| 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 |
| CN210715257U (en) * | 2019-07-24 | 2020-06-09 | 深圳市柏英特电子科技有限公司 | Magnetic suspension turbine rotor structure beneficial to dynamic balance test |
| CN111485958A (en) * | 2020-04-20 | 2020-08-04 | 山东交通学院 | Tip coating for a gas turbine engine blade |
| CN213928460U (en) * | 2020-12-31 | 2021-08-10 | 南昌航空大学 | High-temperature-resistant turbine disc based on ceramic material |
-
2020
- 2020-12-31 CN CN202011631858.XA patent/CN112576314A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4362775A (en) * | 1979-07-05 | 1982-12-07 | Toray Industries, Inc. | Polyester film-heat-bonded metal sheet and container made thereof |
| CN101125753A (en) * | 2006-06-08 | 2008-02-20 | 苏舍美特科（美国）公司 | Dysprosia stabilized zirconia abradable |
| CN104769228A (en) * | 2012-11-06 | 2015-07-08 | 西门子能量股份有限公司 | Turbine airfoil abradable coating system and corresponding turbine blades |
| CN105452530A (en) * | 2013-08-08 | 2016-03-30 | 索拉透平公司 | High porosity abradable coating |
| CN106968716A (en) * | 2016-11-21 | 2017-07-21 | 北京航空航天大学 | Ceramic matric composite turbine blisks |
| CN210715257U (en) * | 2019-07-24 | 2020-06-09 | 深圳市柏英特电子科技有限公司 | Magnetic suspension turbine rotor structure beneficial to dynamic balance test |
| 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 |
| CN111485958A (en) * | 2020-04-20 | 2020-08-04 | 山东交通学院 | Tip coating for a gas turbine engine blade |
| CN213928460U (en) * | 2020-12-31 | 2021-08-10 | 南昌航空大学 | High-temperature-resistant turbine disc based on ceramic material |
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