CN107035420A - A kind of turbine disk - Google Patents
A kind of turbine disk Download PDFInfo
- Publication number
- CN107035420A CN107035420A CN201710396143.2A CN201710396143A CN107035420A CN 107035420 A CN107035420 A CN 107035420A CN 201710396143 A CN201710396143 A CN 201710396143A CN 107035420 A CN107035420 A CN 107035420A
- Authority
- CN
- China
- Prior art keywords
- blade
- passage
- wheel disc
- turbine disk
- cavity
- Prior art date
- 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.)
- Pending
Links
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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- 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
- F01D5/025—Fixing blade carrying members on shafts
-
- 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
Abstract
The invention provides a kind of turbine disk, including multiple blades and wheel disc, cavity is offered in the blade, the multiple blade is integrally formed with the wheel disc by welding procedure.The turbine disk of an embodiment of the present invention, reduces number of components compared to existing turbine disk, improves reliability.
Description
Technical field
The present invention relates to a kind of turbine disk, the turbine disk that specially a kind of structure efficiency is high, reliability is high.
Background technology
For the lightweight, long lifespan of turbine rotor requirement in aero-engine or other gas-turbine units, reliably
Property it is high.The structure of existing turbine disk as shown in Figures 1 to 3, including：It is blade 1, wheel disc 2, flow guiding disc 3, cold gas entering opening 4, cold
Gas passage 5.Wherein, blade 1 and wheel disc 2 are connected using dovetail manner.Flow guiding disc 3 is arranged at the side of wheel disc 2, in flow guiding disc 3
Cold air path 5 is formed between wheel disc 2.The cold gas entering opening 4 being connected with cold air path 5 is provided with flow guiding disc 3, gas is cooled down
Body enters cold air path 5 by cold gas entering opening 4, and is upwardly into blade 1 along cold air path 5, and blade 1 is cooled down.
Be solid inside above-mentioned existing wheel disc, not all position answers dynamics all very high at work, it is internal some
The stress at position is relatively small so that the utilization rate of material is not high, and structure efficiency is relatively low, causes to take turns disk stress under many circumstances
Higher or weight is laid particular stress on.
In addition, blade and wheel disc are separated and lobe numbers are more, therefore number of parts is more.And turbine rotor need to be mixed
Flow guiding disc so that number of parts further increases, causes reliability to reduce.Blade and wheel disc are connected by tenon structure, technique ring
Section is more, required precision height, and the process-cycle is longer, cost is higher.
The content of the invention
A primary object of the present invention is providing a kind of turbine disk, including multiple blades and wheel disc, in the leaf
Cavity is offered in piece, the multiple blade is integrally formed with the wheel disc by welding procedure.
According to an embodiment of the present invention, a plurality of center from the wheel disc is offered in the wheel disc to extending around
Cold air path, every cold air path corresponds to a blade, and is connected with the cavity in the blade.
According to an embodiment of the present invention, the angle of the cold air path and the turbine disk rotary shaft be 45~
90°。
According to an embodiment of the present invention, a toroidal cavity, a plurality of first passage and many are offered in the wheel disc
The passage of bar second；The toroidal cavity is centrally disposed around the wheel disc, and first passage connects the toroidal cavity
With the wheel disk center, second passage connects the toroidal cavity and the blade cavity；The cold air path is by institute
State the first passage, the toroidal cavity and second passage composition.
According to an embodiment of the present invention, the cross sectional shape of first passage and/or second passage is circle
Shape, ellipse or the rectangle with chamfering.
According to an embodiment of the present invention, the number of the first passage is four, the number of second passage and institute
The number for stating blade is identical.
According to an embodiment of the present invention, the welding procedure is diffusion welding (DW).
According to an embodiment of the present invention, the blade is made using resistance to monocrystal material, and the wheel disc uses powdered-metal
It is made.
According to an embodiment of the present invention, blade body, blade listrium and the blade that the blade includes being sequentially connected are stretched
Root, the blade stretches root bead by the blade and is connected to the wheel disc.
The turbine disk of an embodiment of the present invention, number of components is reduced compared to existing turbine disk, is improved
Reliability.
Brief description of the drawings
Fig. 1 is the blade of existing turbine disk and the schematic cross-section of wheel disc；
Fig. 2 is Fig. 1 blade and the feather joint partial schematic diagram of wheel disc；
Fig. 3 is the cold air circulation schematic diagram of existing turbine disk；
Fig. 4 is the schematic cross-section of the turbine disk of an embodiment of the present invention；
Fig. 5 is the cold air circulation schematic diagram in the turbine disk of an embodiment of the present invention.
Embodiment
Embodying the exemplary embodiment of feature of present invention and advantage will describe in detail in the following description.It should be understood that
The present invention can have various changes in different embodiments, and it is neither departed from the scope of the present invention, and theory therein
Bright and diagram is treated as purposes of discussion in itself, and is not used to the limitation present invention.Involved in the present invention " on " " under " " left side "
The orientation such as " right side " term, is the description carried out with reference to the orientation of device in accompanying drawing, not limitation of the invention.
As shown in Figure 4,5, the turbine disk of an embodiment of the present invention, including multiple blades 10 and wheel disc 20, blade
10 with wheel disc 20 by welded shaping, the welding procedure for example can be diffusion welding (DW).Wheel disc 20 is a round, Duo Geye
Piece 10 can be distributed evenly in the circumferential edge of wheel disc.
Blade 10 may include that the blade body 11 being sequentially connected, blade listrium 12 and blade stretch root 13, in blade body 11
Cavity 111 is inside offered, reinforcement 112,113 is provided with cavity 111, is further opened with blade body 11 outside connection
Multiple ventholes 114 and multiple trailing edge ventholes 115.
Reinforcement 112,113 can be bar shape, and specific size can be according to the location of its and the phase of cavity 111
Match somebody with somebody, the concrete shape in its section can also be selected as needed.Reinforcement 112 is in vertical bar shaped, is arranged in cavity 111
Portion, cavity 111 is obstructed into the two parts being connected.The top of reinforcement 112 is connected to the top of blade body 11, two sides
Face is individually fixed in the leading flank and trailing flank of blade body 11 (leading flank and trailing flank are overlapping in Fig. 4).Reinforcement 113 is tool
There is the bar shape of a flex point, be arranged at cavity 111 and be reinforced in the left side cavity of the barrier of muscle 112, and further by left side cavity
It is separated into the two parts being connected.Reinforcement 113 is individually fixed in the leading flank and rear side of blade body 11 by two sides
Face.The setting of reinforcement 112,113 can not only strengthen the intensity of hollow blade 10, can also play shunting to cooling gas
Effect.
Multiple ventholes 114 are offered at the top of blade body 11, the right side of blade body 11 is provided with multiple tails
Edge venthole 115, venthole 114 and trailing edge venthole 115 are opened up so that cavity 111 keeps circulating with extraneous.
Blade 10 can be stretched root 13 by blade and be welded in wheel disc 20 so that blade 10 is integrally formed with wheel disc 20, wherein Fig. 4
The dotted line that Leaf stretches the bottom of root 13 represents sealing wire.So that the number of parts is reduced, reliability is improved.Leaf
The material of piece 10 and wheel disc 20 can be metal, and they can be identical metal or different metals, be preferably
Different metals.Blade 10 can use exotic material, such as such as monocrystalline or isometric crystal material, DD3, DD6, DZ125.Wheel disc
20 can use high intensity, antifatigue material, can be powdered-metal, such as FGH95, FGH96.
Offered in wheel disc 20 a plurality of center from wheel disc 20 respectively to extend around and through wheel disc 20 cold air lead to
Road, each blade 10 has a corresponding cold air path.Cold air path and turbine disk rotary shaft OO ' angle can be 45
~90 °, the rotary shaft OO ' of preferably 90 °, i.e. cold air path preferably with turbine disk is perpendicular.Each cold air path can
It is made up of three parts：Passage 21, cavity 22 and passage 23.Wheel disc 20 is a cylindrical ring body, and rotary shaft OO ' can be located at wheel disc
20 center, can open up a plurality of passage 21 extended from center to circumferential edge on wheel disc 20, every passage 21 with
Cavity 22 is connected.The number of passage 21 can be for 2,4 or identical with the number of blade 10.Passage 21 and rotation
Rotating shaft OO ' angle can be 45~90 °, and preferably passage 21 is perpendicular to rotary shaft OO '.Further, the institute of passage 21
The position at place is preferably that the length by wheel disc 20 along rotary shaft OO ' directions is divided into equal two parts, i.e. Fig. 4 positioned at passage 21
The thickness of the wheel disc in left side is equal with the thickness of the wheel disc positioned at the right side of passage 21.The cross sectional shape of passage 21 can be round
Shape, ellipse or the rectangle with chamfering, the cold air flow that the gross area can need according to blade 10 are determined.
Cavity 22 is a toroidal cavity, centered on the center of wheel disc 20.Cavity 22 is arranged at passage 21 and passage
Between 23, location is preferably that the length by wheel disc 20 along rotary shaft OO ' directions is divided into equal two parts, i.e., positioned at cavity
The thickness of the wheel disc 20 of 22 both sides (along OO ' directions) is equal.In addition, the concrete shape and volume of cavity 22 can be according to being actually needed
Depending on.The setting of cavity 22 is removed equivalent to the less region of the internal stress of wheel disc 20, can effectively mitigate turbine disk
Overall weight, reduces structural stress, improves structure efficiency, extends the wheel disc life-span, shortens the process-cycle, improves economy.
A plurality of passage 23 is opened in the marginal portion of wheel disc 20, and the quantity of passage 23 is identical with the quantity of blade 10,
Every passage 23 is respectively communicated in cavity 22 and cavity 111.Direction, cross sectional shape of passage 23 etc. can be with passages 21
It is identical.Preferably, passage 23 is on same straight line with corresponding passage 21.
As shown in figure 5, during operation, cooling gas enters cavity 22 by passage 21, and further passes through passage 23
Into blade 10.In the presence of reinforcement 112,113, the cooling gas into cavity 111 is split, and part cooling gas is led to
Cross the venthole 114 positioned at the top of blade body 11 to flow out, another part gas is flowed out by trailing edge venthole 115, wherein Fig. 5
The flow direction for being oriented to cold air of middle arrow.
The turbine disk of an embodiment of the present invention is compared with Fig. 1 to Fig. 3 existing turbine disk, full
On the basis of sufficient intensity requirement, weight saving>8%, stress reduction>10%, resultant effect is clearly.
Unless limited otherwise, term used herein is the implication that those skilled in the art are generally understood that.
Embodiment described in the invention is not used to limit the scope of the invention merely for exemplary purpose,
Those skilled in the art can be made within the scope of the invention various other replacements, changes and improvements, thus, the invention is not restricted to
Above-mentioned embodiment, and be only defined by the claims.
Claims (9)
1. a kind of turbine disk, including multiple blades and wheel disc, offer cavity in the blade, the multiple blade with
The wheel disc is integrally formed by welding procedure.
2. turbine disk according to claim 1, wherein being offered in the wheel disc a plurality of from the wheel disc
The heart is to the cold air path extended around, and every cold air path corresponds to a blade, and is connected with the cavity in the blade.
3. turbine disk according to claim 2, wherein the cold air path and the turbine disk rotary shaft
Angle is 45~90 °.
4. turbine disk according to claim 2, wherein offering a toroidal cavity, a plurality of first in the wheel disc
Passage and a plurality of second passage；The toroidal cavity is centrally disposed around the wheel disc, and first passage connects institute
Toroidal cavity and the wheel disk center are stated, second passage connects the toroidal cavity and the blade cavity；It is described cold
Gas passage is made up of first passage, the toroidal cavity and second passage.
5. turbine disk according to claim 4, wherein section of first passage and/or second passage
Face is shaped as circular, the oval or rectangle with chamfering.
6. turbine disk according to claim 4, the number of first passage is four, second passage
Number it is identical with the number of the blade.
7. turbine disk according to claim 1, wherein the welding procedure is diffusion welding (DW).
8. turbine disk according to claim 1, wherein the blade is made using resistance to monocrystal material, the wheel disc is adopted
It is made with powdered-metal.
9. turbine disk according to claim 1, wherein the leaf packet includes the blade body being sequentially connected, blade edge
Plate and blade stretch root, and the blade stretches root bead by the blade and is connected to the wheel disc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710396143.2A CN107035420A (en) | 2017-05-27 | 2017-05-27 | A kind of turbine disk |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710396143.2A CN107035420A (en) | 2017-05-27 | 2017-05-27 | A kind of turbine disk |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107035420A true CN107035420A (en) | 2017-08-11 |
Family
ID=59540186
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710396143.2A Pending CN107035420A (en) | 2017-05-27 | 2017-05-27 | A kind of turbine disk |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107035420A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3982852A (en) * | 1974-11-29 | 1976-09-28 | General Electric Company | Bore vane assembly for use with turbine discs having bore entry cooling |
| US5961287A (en) * | 1997-09-25 | 1999-10-05 | United Technologies Corporation | Twin-web rotor disk |
| CN101896311A (en) * | 2007-12-22 | 2010-11-24 | Mtu飞机发动机有限公司 | Method for the production of an integrally bladed rotor, and rotor |
| CN102102544A (en) * | 2011-03-11 | 2011-06-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Turbine rotor blade of gas turbine |
| CN104191184A (en) * | 2014-08-15 | 2014-12-10 | 中国燃气涡轮研究院 | Anti-vibration type dual-alloy turbine blisk and manufacturing method thereof |
| CN106014485A (en) * | 2016-07-01 | 2016-10-12 | 中航空天发动机研究院有限公司 | Flow guide and cooling structure applied to double-wheel-disc turbine disk cavity |
-
2017
- 2017-05-27 CN CN201710396143.2A patent/CN107035420A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3982852A (en) * | 1974-11-29 | 1976-09-28 | General Electric Company | Bore vane assembly for use with turbine discs having bore entry cooling |
| US5961287A (en) * | 1997-09-25 | 1999-10-05 | United Technologies Corporation | Twin-web rotor disk |
| CN101896311A (en) * | 2007-12-22 | 2010-11-24 | Mtu飞机发动机有限公司 | Method for the production of an integrally bladed rotor, and rotor |
| CN102102544A (en) * | 2011-03-11 | 2011-06-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Turbine rotor blade of gas turbine |
| CN104191184A (en) * | 2014-08-15 | 2014-12-10 | 中国燃气涡轮研究院 | Anti-vibration type dual-alloy turbine blisk and manufacturing method thereof |
| CN106014485A (en) * | 2016-07-01 | 2016-10-12 | 中航空天发动机研究院有限公司 | Flow guide and cooling structure applied to double-wheel-disc turbine disk cavity |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170811 |
|
| RJ01 | Rejection of invention patent application after publication |