CN107152311A - The turbine disk, engine and aircraft - Google Patents
The turbine disk, engine and aircraft Download PDFInfo
- Publication number
- CN107152311A CN107152311A CN201710391746.3A CN201710391746A CN107152311A CN 107152311 A CN107152311 A CN 107152311A CN 201710391746 A CN201710391746 A CN 201710391746A CN 107152311 A CN107152311 A CN 107152311A
- Authority
- CN
- China
- Prior art keywords
- disk
- turbine disk
- cavity
- turbine
- engine
- 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.)
- Granted
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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
- F01D5/02—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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
Abstract
The present invention relates to engine art, disclose a kind of turbine disk, engine and aircraft, the turbine disk includes left disk and right disk positioned opposite to each other, the left disk and right disk side relative to each other are respectively formed with concave part and are formed as cavity can mutually fasten, and the cavity is communicated in external environment condition by the passage through extension.Cavity is formed with the turbine disk of the present invention, thus, it is possible to reduce weight, is adapted to lightweight growth requirement.Also, due to being provided with the passage of connection cavity and external environment condition, it is allowed to which air is freely accessible in cavity or from cavity discharge, thus will not because it expands with heat and contract with cold and recurring structure is deformed.
Description
Technical field
The present invention relates to engine art, in particular it relates to a kind of turbine disk.On this basis, the invention further relates to one
Plant the engine with the turbine disk and the aircraft with the engine.
Background technology
Constantly aggravate with the competition of aircraft industry, for the turbine in aero-engine (or other gas-turbine units)
Disk develops to lightweight.But in order to which with higher safety and reliability, the structure design of the turbine disk is also by larger office
Limit.
Fig. 1 show the attachment structure schematic diagram of the turbine disk 1 and blade 2 in a kind of conventional art.Wherein, the turbine disk 1
For solid construction, with higher weight, be not suitable for lightweight growth requirement.In this regard, proposing as shown in Figure 2 has cavity
11 and it is connected with the turbine disk 1 of blade 2, it is possible to avoid the region of answering dynamics higher by being appropriately arranged with the position of cavity 11
With solid material, thus with higher stock utilization, and ensure reliability needs.
However, setting cavity 11 to need to connect by welding manner in the turbine disk 1, for example, weld seam 12 is arranged on symmetrically
Position, this easily causes malformation larger in welding process, influences parts precision, and high with complicated technique, cost
And the process-cycle is long.In addition, after by being welded to connect, the inner sealing of cavity 11 accommodates air, in use easily due to
Expand with heat and contract with cold and cause the malformation of the turbine disk 1.
Above- mentioned information is only used for strengthening the understanding of the background to the present invention disclosed in the background section.
The content of the invention
A primary object of the present invention is to overcome at least one defect of above-mentioned prior art, and there is provided a kind of not variable
Shape and the turbine disk with lower weight.
Another main purpose of the present invention is to overcome at least one defect of above-mentioned prior art to have there is provided one kind
The engine and aircraft of the turbine disk.
According to an aspect of the present invention there is provided a kind of turbine disk, the turbine disk include left disk positioned opposite to each other and
Right disk, the left disk and right disk side relative to each other are respectively formed with concave part and are formed as cavity can mutually fasten, the sky
Chamber is communicated in external environment condition by the passage through extension.
According to an embodiment of the present invention, wherein the left disk and right disk are on surface that is relative to each other and being bonded with each other
The ventilating part radially extended is respectively formed with, the ventilating part is fastened each other is formed as the passage.
According to an embodiment of the present invention, wherein the turbine disk has the tongue-and-groove for being used for connecting blade, at least partly
The passage extends to the bottom land of the tongue-and-groove from the cavity.
According to an embodiment of the present invention, wherein the left disk and right disk have hub portion, disc portion and outer company respectively
Socket part, the cavity is located at the disc portion and the hub portion, and tapered in a radially inward direction in the hub portion.
According to an embodiment of the present invention, wherein the left disk and right disk are on surface that is relative to each other and being bonded with each other
Location structure is respectively formed with, the location structure includes the positioning extended from one of the left disk and right disk to another one
Pin.
According to an embodiment of the present invention, wherein the location structure is included in circumferentially uniform multigroup of the turbine disk
The alignment pin.
According to an embodiment of the present invention, alignment pin includes the radial direction for being arranged at the cavity respectively wherein described in each group
The alignment pin of both sides first and the second alignment pin.
According to another aspect of the present invention, a kind of engine is also provided, the engine includes multiple hairs being coaxially disposed
The above-mentioned turbine disk of bright offer.
According to an embodiment of the present invention, the center of wherein each turbine disk is respectively formed with tie rod hole, pull bar
Extend through the tie rod hole and be applied with axial pre tightening force on the turbine disk.
According to another aspect of the present invention, a kind of aircraft with above-mentioned engine is also provided.
The advantage and beneficial effect of the turbine disk, engine and aircraft that the present invention is provided are：By above-mentioned technical proposal,
Cavity is formed with the turbine disk of the present invention, thus, it is possible to reduce weight, is adapted to lightweight growth requirement.Also, due to setting
It is equipped with connection cavity and the passage of external environment condition, it is allowed to which air is freely accessible in cavity or from cavity discharge, thus will not
Because it expands with heat and contract with cold and recurring structure deform.
Brief description of the drawings
By being considered in conjunction with the accompanying following the following detailed description of the embodiment of the present invention, various targets of the invention,
Feature and advantage will become apparent.Accompanying drawing is only the exemplary diagram of the present invention, is not necessarily drawn to scale.
In the accompanying drawings, same reference represents same or similar part all the time.Wherein：
Fig. 1 is the attachment structure schematic diagram according to a kind of turbine disk and blade in conventional art；
Fig. 2 is the attachment structure schematic diagram according to another turbine disk and blade in conventional art；
Fig. 3 is the attachment structure schematic diagram of the turbine disk according to a kind of preferred embodiment of the invention and blade；
Fig. 4 is the dimensional structure diagram of the turbine disk in Fig. 3；
Fig. 5 is the dimensional structure diagram from the turbine disk in Fig. 3 of another view；
Fig. 6 is the dimensional structure diagram from the turbine disk in Fig. 3 of another view；
Fig. 7 is that the turbine disk is attached to structural representation when in engine in Fig. 3.
Description of reference numerals：
1st, the turbine disk；11st, cavity；
12nd, weld seam；13rd, left disk；
14th, right disk；15th, passage；
16th, tongue-and-groove；17th, alignment pin；
171st, the first alignment pin；172nd, the second alignment pin；
101st, hub portion；102nd, disc portion；
103rd, outer connecting portion；2nd, blade；
3rd, pull bar.
Embodiment
Example embodiment is described more fully with referring now to accompanying drawing.However, example embodiment can be with a variety of shapes
Formula is implemented, and is not understood as limited to embodiment set forth herein；On the contrary, thesing embodiments are provided so that the present invention will
Fully and completely, and by the design of example embodiment those skilled in the art is comprehensively conveyed to.Identical accompanying drawing in figure
Mark represents same or similar structure, thus will omit their detailed description.
With reference to shown in Fig. 3 to Fig. 7, according to a kind of turbine disk 1 of preferred embodiment of the invention, one is generally integrally formed into
Disk-like structure is planted, to be rotated around its center axis.The turbine disk 1 of the present invention includes left disk 13 and right disk positioned opposite to each other
14, the two side relative to each other is respectively formed with concave part, is formed as with can mutually fasten such as the cavity 11 of annular.The sky
Chamber 11 is communicated in external environment condition by the passage 15 through extension." through extension " described herein refers to that the extension of passage 15 is logical
The whole wall thickness part of the cladding cavity 11 of the turbine disk 1 is crossed, the external environment condition refers to the region comparatively opened, such as then
Described bottom land of tongue-and-groove 16 etc..By above-mentioned setting, the cavity 11 formed in the turbine disk 1 can reduce weight, be adapted to light
Quantify growth requirement.Also, due to being provided with the passage 15 of connection cavity 11 and external environment condition, it is allowed to which air is freely accessible to sky
Discharge in chamber 11 or from the cavity 11, thus will not because it expands with heat and contract with cold and recurring structure is deformed.
Above-mentioned passage 15 and cavity 11 can be formed at any appropriate location or structure.Wherein, can for the ease of shaping
To be respectively formed with the ventilating part radially extended on the surface that left disk 13 and right disk 14 are relative to each other and are bonded with each other, this leads to
Gas portion fastens to form passage 15 each other.For example, can left disk 13 and right disk 14 from its constitute the concave part of cavity 11 to
Deep-slotted chip breaker (ventilating part) is formed on the surface of radial outer end and/or the inner, it is possible thereby to form round vent 15.Thus, structure
Ventilating part into passage 15 can be readily formed by modes such as casting, machinings, and processing technology is simple.
As shown in Figure 3, Figure 5 and Figure 6, generally there is the turbine disk 1 tongue-and-groove 16 and tenon tooth that are used to connect blade 2 (not to mark
Note) etc., wherein, the bottom land from cavity 11 to tongue-and-groove 16 sets some passage 15.Another part passage 15 is from cavity
11 extend to the tie rod hole of center position, as shown in Figures 3 to 5.
With continued reference to Fig. 3, Fig. 5 and Fig. 6, set cavity 11 structural strength may be caused to be deteriorated in the turbine disk 1, therefore need
It is appropriately arranged with the location and shape of cavity 11 wherein etc..As shown in figure 4, for convenience of description, by left disk 13 and right disk 14
It is divided into the hub portion 101 being sequentially arranged from center to outer rim, disc portion 102 and outer connecting portion 103.The outer connecting portion 103 can be with
Tongue-and-groove is formed, for connecting blade 2；Hub portion 101 surround and forms tie rod hole.The plane cutting for passing through its center axis when edge
Afterwards, the partial cross sectional of the turbine disk 1 is the structure shown in Fig. 3.Wherein, because the mid-depth position of disc portion 102 is basic
Stress will not be produced, and generally the thickness of hub portion 101 is along towards center position increase, therefore, the present invention sets cavity 11
In two parts, and it is tapered in a radially inward direction in hub portion 101.
Reference picture 3 to Fig. 5, according to it is of the invention it is a kind of more preferred embodiment in, left disk 13 and right disk 14 are at that
Location structure is also respectively formed with this relative and surface for being bonded with each other, the location structure is included from left disk 13 and right disk 14
One of the alignment pin 17 that extends to another one.The alignment pin 17 can be integrally formed with left disk 13 or right disk 14 or is connected in advance
To one of which, and form in another one the positioning hole for coordinating with the alignment pin 17.Thus, it is possible to fast in connection
Speed accurately determines assembling position, is easy to improve efficiency of assembling.Alignment pin 17 can also play a part of transmitting portions moment of torsion.
Can have the multigroup alignment pin 17 being evenly distributed, such as 2 groups, 3 groups, 4 groups on the turbine disk 1.Its group of number can be with
It is configured to divide exactly the number of blade to be connected.
With continued reference to Fig. 3 to Fig. 5, each group alignment pin 17 can be arranged in different radial positions, preferably to play
Positioning action.For example, in illustrated preferred embodiment, alignment pin 17 includes being arranged on the first positioning of the radially opposite sides of cavity 11
The alignment pin 172 of pin 171 and second.Wherein, the first alignment pin 171 can be located on the projection for constituting tongue-and-groove 16, the second alignment pin
172 can be arranged in above-mentioned hub portion 101.
The turbine disk 1 that the present invention is provided is described in detail above, on this basis, the present invention is also provided with many
The engine of the individual above-mentioned turbine disk 1, the plurality of turbine disk 1 is set coaxially to each other, as shown in Figure 7.
If however, the left disk 13 and right disk 14 of the turbine disk 1 are connected yet by modes such as welding, easily because of local heating's mistake
Height causes deterioration in accuracy.In this regard, in a kind of engine of preferred embodiment, the center of each turbine disk 1 is respectively formed with
Tie rod hole, pull bar 3 extends through the tie rod hole, to cause left disk 13 and right disk 14 fits each other compression, and has axial pretightening
Power F.By this set, parts precision can be effectively improved, and significantly shortens the process-cycle, improve economy.It is demonstrated experimentally that
Cavity 11 and the turbine disk 1 connected by pull bar 3 are provided with, about 8% weight can be mitigated, and stress is reduced about 10%,
Achieve significant resultant effect.
In addition, the present invention also provides a kind of aircraft with above-mentioned engine.
Feature, structure or characteristic described in the invention can be combined in any suitable manner to be implemented one or more
In mode.Embodiments of the present invention are fully understood so as to provide there is provided many details in superincumbent description.So
And, it will be appreciated by persons skilled in the art that technical scheme can be put into practice without one in the specific detail
Or more, or can be using other methods, component, material etc..In other cases, it is not shown in detail or describes known knot
Structure, material operate to avoid fuzzy each aspect of the present invention.
Claims (10)
1. a kind of turbine disk, it is characterised in that the turbine disk includes left disk and right disk positioned opposite to each other, the left disk and right disk
Side relative to each other is respectively formed with concave part and is formed as cavity can mutually fasten, and the cavity passes through through the logical of extension
Stomata is communicated in external environment condition.
2. the turbine disk according to claim 1, it is characterised in that the left disk and right disk toward each other and are being bonded with each other
Surface on be respectively formed with the ventilating part radially extended, the ventilating part is fastened each other is formed as the passage.
3. the turbine disk according to claim 1, it is characterised in that the turbine disk has the tongue-and-groove for being used for connecting blade,
At least partly described passage extends to the bottom land of the tongue-and-groove from the cavity.
4. the turbine disk according to claim 1, it is characterised in that the left disk and right disk have hub portion, spoke respectively
Portion and outer connecting portion, the cavity are located at the disc portion and the hub portion, and in the hub portion in a radially inward direction gradually
Contracting.
5. the turbine disk as claimed in any of claims 1 to 4, it is characterised in that the left disk and right disk are each other
Location structure is respectively formed with the relative and surface that is bonded with each other, the location structure is included from one in the left disk and right disk
The alignment pin that person extends to another one.
6. the turbine disk according to claim 5, it is characterised in that it is circumferentially equal that the location structure is included in the turbine disk
Multigroup alignment pin of cloth.
7. the turbine disk according to claim 6, it is characterised in that alignment pin described in each group includes being arranged at the sky respectively
The alignment pin of radially opposite sides first and the second alignment pin of chamber.
8. a kind of engine, it is characterised in that the engine is multiple according to any in claim 1 to 7 including what is be coaxially disposed
The turbine disk described in one.
9. engine according to claim 8, it is characterised in that the center of each turbine disk is respectively formed with pull bar
Hole, pull bar extends through the tie rod hole and is applied with axial pre tightening force on the turbine disk.
10. a kind of aircraft, it is characterised in that the aircraft has engine according to claim 8 or claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710391746.3A CN107152311B (en) | 2017-05-27 | 2017-05-27 | The turbine disk, engine and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710391746.3A CN107152311B (en) | 2017-05-27 | 2017-05-27 | The turbine disk, engine and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107152311A true CN107152311A (en) | 2017-09-12 |
| CN107152311B CN107152311B (en) | 2019-11-19 |
Family
ID=59793826
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710391746.3A Active CN107152311B (en) | 2017-05-27 | 2017-05-27 | The turbine disk, engine and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107152311B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114368469A (en) * | 2020-10-16 | 2022-04-19 | 中航西飞民用飞机有限责任公司 | Airplane airfoil composite material wing tip structure and manufacturing method |
Citations (5)
| 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 |
| JPH0988506A (en) * | 1995-09-21 | 1997-03-31 | Ngk Insulators Ltd | Blade for hybrid type gas turbine moving blade and turbine disc and hybrid type gas turbine moving blade consisting of them |
| JPH10252403A (en) * | 1997-03-12 | 1998-09-22 | Mitsubishi Heavy Ind Ltd | Cooling device of gas turbine |
| US5961287A (en) * | 1997-09-25 | 1999-10-05 | United Technologies Corporation | Twin-web rotor disk |
| 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 CN201710391746.3A patent/CN107152311B/en active Active
Patent Citations (5)
| 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 |
| JPH0988506A (en) * | 1995-09-21 | 1997-03-31 | Ngk Insulators Ltd | Blade for hybrid type gas turbine moving blade and turbine disc and hybrid type gas turbine moving blade consisting of them |
| JPH10252403A (en) * | 1997-03-12 | 1998-09-22 | Mitsubishi Heavy Ind Ltd | Cooling device of gas turbine |
| US5961287A (en) * | 1997-09-25 | 1999-10-05 | United Technologies Corporation | Twin-web rotor disk |
| 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 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114368469A (en) * | 2020-10-16 | 2022-04-19 | 中航西飞民用飞机有限责任公司 | Airplane airfoil composite material wing tip structure and manufacturing method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107152311B (en) | 2019-11-19 |
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