CN106089311B - The bar jointing structure of gas turbine rotor wheel disc - Google Patents
The bar jointing structure of gas turbine rotor wheel disc Download PDFInfo
- Publication number
- CN106089311B CN106089311B CN201610663951.6A CN201610663951A CN106089311B CN 106089311 B CN106089311 B CN 106089311B CN 201610663951 A CN201610663951 A CN 201610663951A CN 106089311 B CN106089311 B CN 106089311B
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- Prior art keywords
- tie rod
- pull bar
- elastic component
- gas turbine
- rod hole
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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
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to gas turbine technology field, more particularly to a kind of bar jointing structure of gas turbine rotor wheel disc, including pull bar, rotor disk and elastic component, pull bar is provided with circumferentially raised annular convex shoulder；Offered on rotor disk axially through tie rod hole；Circumference of the elastic component along tie rod hole is on the hole wall of tie rod hole；Pull bar is arranged in tie rod hole, and the outer peripheral face of annular convex shoulder contacts with elastic component.Elastic component is set between the annular convex shoulder of pull bar and the tie rod hole hole wall of rotor disk, so that annular convex shoulder does not contact directly with tie rod hole hole wall, during gas turbine operation, when pull bar is occured bending and deformation by centrifugal action, elastic component will provide damping, it can suppress to draw vibration of bar, while reduce the stress concentration of pull bar and rotor disk assembling contact area, be advantageous to the safe operation of gas turbine unit, improve the bulk life time of rotor disk and pull bar.
Description
Technical field
The present invention relates to the pull bar connection knot of gas turbine technology field, more particularly to a kind of gas turbine rotor wheel disc
Structure.
Background technology
At present, the structural shape of heavy duty gas turbine rotor is varied, is roughly divided into drum, disc type and disk drum-type and turns
Sub- three types.Wherein, disk drum type rotor combines the advantages of drum rotor and disk rotor：It is in wheel rim or close to wheel rim
Place is rotary drum, and rigidity is good, and then roller disk is born centrifugal force, thus intensity is high.In addition, disk drum type rotor also has weight small
Advantage.Therefore, disk drum type rotor is most widely used in the gas turbine.
Disk drum type rotor mainly has pull bar combination order drum-type and the major class of welded type two at present.Welded type rotor is multistage wheel disc
It is welded, no mechanical connection, heat coordinates and run through bolt, and for any part of rotor all without the relative changing of the relative positions occurs, structure can
Lean on, intensity is good, but its welding process requirement is strict, and technical threshold is high.Pull bar composite fabricated rotor includes circumferential pull bar combined type
And central draw bar type, pull bar combined rotor structure provides pretightning force by pull bar, by end-tooth or rubbing surface torsion pass.
In the prior art, gas turbine circumference pull bar is generally pole type structure, and the opening position of itself and wheel disc assembling is processed
For cylindrical type convex shoulder, several tie rod holes being engaged with pull bar convex shoulder are then machined with wheel disc, and tie rod hole is processed as circular hole,
Cylindrical type convex shoulder on pull bar and the tie rod hole on wheel disc are typical round cooperation.When gas turbine rotor is run, pull bar
On convex shoulder and wheel disc on the contact form of tie rod hole be linear contact lay so that the stress concentration of wheel disc upper connecting rod hole location compared with
To be obvious, pull bar and sheave contact regional stress are excessive, can damage pull bar and wheel disc, are unfavorable for gas turbine safe operation.
The content of the invention
It can suppress pull bar vibration the technical problem to be solved in the present invention is to provide one kind, reduce pull bar and sheave contact area
The bar jointing structure of the gas turbine rotor wheel disc of domain stress concentration, to overcome the drawbacks described above of prior art.
In order to solve the above-mentioned technical problem, the present invention adopts the following technical scheme that：A kind of drawing of gas turbine rotor wheel disc
Bar attachment structure, including pull bar, rotor disk and elastic component, pull bar are provided with circumferentially raised annular convex shoulder；Rotor disk
On offer axially through tie rod hole；Circumference of the elastic component along tie rod hole is on the hole wall of tie rod hole；Pull bar is arranged in drawing
Rod aperture, and the outer peripheral face of annular convex shoulder contacts with elastic component.
Preferably, annular convex shoulder is interference fitted with elastic component.
Preferably, the hole wall of tie rod hole is provided with groove, and elastic component is embedded at groove.
Preferably, elastic component is welded on the hole wall of tie rod hole.
Preferably, elastic component is in a ring.
Preferably, width of the elastic component along tie rod hole axial direction is not less than the width of annular convex shoulder outer peripheral face.
Preferably, elastic component is made of metal-rubber.
More preferably, the tie rod hole on pull bar and rotor disk is equipped with multiple, circumference of multiple tie rod holes along rotor disk
It is uniformly distributed and is corresponded with multiple pull bars.
More preferably, the annular convex shoulder on rotor disk and pull bar is equipped with multiple, and multiple rotor disks are coaxially disposed in drawing
Corresponded on bar and with multiple annular convex shoulders.
More preferably, the end of pull bar is provided with and tightens nut.
Compared with prior art, the present invention has significant progressive：
By setting elastic component between the annular convex shoulder of pull bar and the tie rod hole hole wall of rotor disk so that annular convex shoulder
Do not contacted directly with tie rod hole hole wall, during gas turbine operation, when pull bar is occured bending and deformation by centrifugal action, bullet
Property part damping will be provided, can suppress to draw vibration of bar, while reduce the stress collection of pull bar and rotor disk assembling contact area
In, be advantageous to the safe operation of gas turbine unit, improve the bulk life time of rotor disk and pull bar.
Brief description of the drawings
Fig. 1 is the assembling schematic diagram of the bar jointing structure of gas turbine rotor wheel disc of the embodiment of the present invention.
Fig. 2 is the elevational schematic in A portions in Fig. 1.
In figure：
100th, rotor disk 101, tie rod hole 102, groove
200th, pull bar 201, annular convex shoulder 300, elastic component
400th, nut is tightened
Embodiment
The embodiment of the present invention is described in further detail below in conjunction with the accompanying drawings.These embodiments are only used for
Illustrate the present invention, and not limitation of the present invention.
In the description of the invention, it is necessary to illustrate, unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or be integrally connected；Can
To be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, above-mentioned term can be understood as the case may be
Concrete meaning in the present invention.
In addition, in the description of the invention, unless otherwise indicated, " multiple " are meant that two or more.
As depicted in figs. 1 and 2, a kind of embodiment of the bar jointing structure of gas turbine rotor wheel disc of the invention.This
The bar jointing structure of the gas turbine rotor wheel disc of embodiment includes pull bar 200, rotor disk 100 and elastic component 300.Its
In, circumferentially raised annular convex shoulder 201 is provided with pull bar 200, offered on rotor disk 100 axially through tie rod hole
101, circumference of the elastic component 300 along tie rod hole 101 is on the hole wall of tie rod hole 101.Pull bar 200 is arranged in tie rod hole 101, and
The outer peripheral face of annular convex shoulder 201 contacts with elastic component 300, i.e., elastic component 300 is located at the hole of annular convex shoulder 201 and tie rod hole 101
Between wall, and annular convex shoulder 201 is wrapped up so that the annular convex shoulder 201 of the pull bar 200 not tie rod hole 101 with rotor disk 100
Hole wall directly contacts.Thus, during gas turbine operation, when pull bar 200 is occured bending and deformation by centrifugal action, elasticity
Part 300 will provide damping, can suppress the vibration of pull bar 200, while reduces pull bar 200 and assemble contact zone with rotor disk 100
The stress concentration in domain, be advantageous to the safe operation of gas turbine unit, improve the bulk life time of rotor disk 100 and pull bar 200.
Preferably, the elastic component 300 in the present embodiment in a ring, the outer peripheral faces of ring elastic parts 300 and tie rod hole 101
Hole wall fitting connects, and the outer peripheral face of the inner peripheral surfaces of ring elastic parts 300 then with annular convex shoulder 201 contacts, so as to by annular convex shoulder
201 excircle is all wrapped within elastic component 300.Certainly, the shape of elastic component is not limited to this implementation in the present invention
The annular of example, other forms can also be used to realize the parcel to annular convex shoulder, such as the elastic component of multiple strips is set,
Circumference of the elastic component of multiple strips along tie rod hole be continuous successively or arranged for interval and form ring-type.
Further, in the present embodiment, width of the elastic component 300 along the axial direction of tie rod hole 101 is not less than outside annular convex shoulder 201
The width of side face, so that in annular convex shoulder 201 can all be wrapped in by elastic component 300, ensure that pull bar 200 occurs bending and deformation
When annular convex shoulder 201 do not contacted directly with the hole wall of tie rod hole 101 all the time.
Further, in order that annular convex shoulder 201 keeps being in close contact with elastic component 300, the annular convex shoulder in the present embodiment
The excircle of annular convex shoulder 201 is less than using interference fit, the i.e. diameter of the inner periphery of elastic component 300 between 201 and elastic component 300
Diameter so that be pressure contact between annular convex shoulder 201 and elastic component 300 after assembling, so as to ensure annular convex shoulder 201 with
Elastic component 300 keeps being in close contact, and is advantageous to strengthen the damping action that elastic component 300 vibrates pull bar 200.
The material of elastic component 300 is not limited in the present embodiment, it is preferred to use elastic component 300 is made in metal-rubber.Metal
Rubber is a kind of by coil of wire spirality, stretched, braiding, extrusion forming, and elasticity that is thermally treated and being formed is more
Porous materials, have the characteristics that high-damping, high resiliency, high temperature resistant, it is corrosion-resistant, be easy to compressing, can be pull bar 200 well
Flexural deformation and vibration provide damping.
In the present embodiment, the hole wall of tie rod hole 101 is provided with groove 102, and circumference of the groove 102 along tie rod hole 101 is in
Annular is set, and elastic component 300 is embedded in groove 102.Thus elastic component 300 can be fixed on the hole wall of tie rod hole 101, and
It is axially displaced along tie rod hole 101 to limit it.When elastic component 300 is made of metal-rubber, can also use elasticity
What the mode that part 300 is welded on the hole wall of tie rod hole 101 realized elastic component 300 and tie rod hole 101 is fixedly connected with and limits elasticity
The axial displacement of part 300, without opening up groove 102 on the hole wall of tie rod hole 101.Certainly, elastic component and pull bar in the present invention
The connected mode of hole hole wall is not limited to the present embodiment, can also be fixedly connected with mode using others.
The bar jointing structure of the gas turbine rotor wheel disc of the present embodiment can be circumferential pull bar combined type, such as Fig. 1 institutes
Show, pull bar 200 be provided with it is multiple, compartment of terrain is provided with multiple annular convex shoulders 201 on each pull bar 200.Correspondingly, rotor disk 100
Also be provided with multiple (not shown)s, multiple rotor disks 100 be coaxially disposed on pull bar 200 and with multiple annular convex shoulders 201
Correspond.Multiple tie rod holes 101, week of multiple tie rod holes 101 along rotor disk 100 are equipped with each rotor disk 100
To being uniformly distributed and corresponded with multiple pull bars 200.It is all provided with the hole wall of each tie rod hole 101 of each rotor disk 100
Flexible part 300.Multiple pull bars 200 sequentially pass through the tie rod hole 101 on multiple rotor disks 100 respectively, make multiple rotor wheels
Disk 100 is assemblied on the annular convex shoulder 201 of pull bar 200 successively.It is equipped with the end of each pull bar 200 and tightens nut 400, is used
Fixed in carrying out axially limitation to it after multiple rotor disks 100 and the assembling of multiple pull bars 200.Rotor in the present embodiment
The quantity of wheel disc 100 and pull bar 200 is not limited to, and should be configured according to actual gas turbine unit.
In summary, the bar jointing structure of the gas turbine rotor wheel disc of the present embodiment, passes through the annular in pull bar 200
Between convex shoulder 201 and the hole wall of tie rod hole 101 of rotor disk 100 set elastic component 300 so that annular convex shoulder 201 not with pull bar
The hole wall of hole 101 directly contacts, during gas turbine operation, when pull bar 200 is occured bending and deformation by centrifugal action, and elasticity
Part 300 will provide damping, can suppress the vibration of pull bar 200, while reduces pull bar 200 and assemble contact zone with rotor disk 100
The stress concentration in domain, be advantageous to the safe operation of gas turbine unit, improve the bulk life time of rotor disk 100 and pull bar 200.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, some improvement and replacement can also be made, these improve and replaced
Also it should be regarded as protection scope of the present invention.
Claims (10)
1. a kind of bar jointing structure of gas turbine rotor wheel disc, it is characterised in that including pull bar (200), rotor disk
(100) and elastic component (300), the pull bar (200) are provided with circumferentially raised annular convex shoulder (201)；The rotor disk
(100) offered on axially through tie rod hole (101)；Circumference of the elastic component (300) along the tie rod hole (101) is located at
On the hole wall of the tie rod hole (101)；The pull bar (200) is arranged in the tie rod hole (101), and the annular convex shoulder
(201) outer peripheral face contacts with the elastic component (300).
2. the bar jointing structure of gas turbine rotor wheel disc according to claim 1, it is characterised in that the convex annular
Shoulder (201) is interference fitted with the elastic component (300).
3. the bar jointing structure of gas turbine rotor wheel disc according to claim 1, it is characterised in that the tie rod hole
(101) hole wall is provided with groove (102), and the elastic component (300) is embedded at the groove (102).
4. the bar jointing structure of gas turbine rotor wheel disc according to claim 1, it is characterised in that the elastic component
(300) it is welded on the hole wall of the tie rod hole (101).
5. the bar jointing structure of gas turbine rotor wheel disc according to claim 1, it is characterised in that the elastic component
(300) in a ring.
6. the bar jointing structure of gas turbine rotor wheel disc according to claim 1, it is characterised in that the elastic component
(300) it is not less than the width of the annular convex shoulder (201) outer peripheral face along the width of the tie rod hole (101) axial direction.
7. the bar jointing structure of gas turbine rotor wheel disc according to claim 1, it is characterised in that the elastic component
(300) it is made of metal-rubber.
8. the bar jointing structure of gas turbine rotor wheel disc as claimed in any of claims 1 to 7, its feature exist
In the tie rod hole (101) on the pull bar (200) and the rotor disk (100) is equipped with multiple, multiple tie rod holes
(101) it is uniformly distributed along the circumference of the rotor disk (100) and is corresponded with multiple pull bars (200).
9. the bar jointing structure of gas turbine rotor wheel disc according to claim 8, it is characterised in that the rotor wheel
Annular convex shoulder (201) on disk (100) and the pull bar (200) is equipped with multiple, and multiple rotor disks (100) coaxially set
It is placed on the pull bar (200) and is corresponded with multiple annular convex shoulders (201).
10. the bar jointing structure of gas turbine rotor wheel disc according to claim 9, it is characterised in that the pull bar
(200) end is provided with and tightens nut (400).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610663951.6A CN106089311B (en) | 2016-08-12 | 2016-08-12 | The bar jointing structure of gas turbine rotor wheel disc |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610663951.6A CN106089311B (en) | 2016-08-12 | 2016-08-12 | The bar jointing structure of gas turbine rotor wheel disc |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106089311A CN106089311A (en) | 2016-11-09 |
| CN106089311B true CN106089311B (en) | 2018-04-03 |
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ID=57456394
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610663951.6A Active CN106089311B (en) | 2016-08-12 | 2016-08-12 | The bar jointing structure of gas turbine rotor wheel disc |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107091156B (en) * | 2017-06-30 | 2018-12-28 | 西安中工动力能源有限公司 | A kind of micro-gas-turbine machine rotor and assembly method |
| CN113125158B (en) * | 2019-12-31 | 2023-04-07 | 中国航发商用航空发动机有限责任公司 | Device for fixing detected shrouded blade and shrouded blade detection equipment |
| CN113027534A (en) * | 2021-04-19 | 2021-06-25 | 清华大学 | Joint surface connecting structure of rotor wheel disc of disc type gas turbine |
| FR3131753A1 (en) * | 2022-01-11 | 2023-07-14 | Safran Aircraft Engines | Improved tie rod turbine rotor and rotor assembly method |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1349170A (en) * | 1970-07-09 | 1974-03-27 | Kraftwerk Union Ag | Rotor for a gas turbine engine |
| US3749516A (en) * | 1971-10-06 | 1973-07-31 | Carrier Corp | Rotor structure for turbo machines |
| FR2317501A1 (en) * | 1975-07-09 | 1977-02-04 | Snecma | COUPLING DEVICE FOR GAS TURBINE ENGINE |
| CN101863428B (en) * | 2010-05-22 | 2013-05-29 | 东方电气集团东方汽轮机有限公司 | Tool special for assembling gas turbine pull rod-type rotor disc and using method thereof |
| CN204716302U (en) * | 2015-04-16 | 2015-10-21 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of turbine wheel disc and turbine rotor |
| CN205895321U (en) * | 2016-08-12 | 2017-01-18 | 上海电气燃气轮机有限公司 | Pull rod connection structure of gas turbine rotor rim plate |
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2016
- 2016-08-12 CN CN201610663951.6A patent/CN106089311B/en active Active
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| CN106089311A (en) | 2016-11-09 |
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