CN107246282A - A kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine - Google Patents
A kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine Download PDFInfo
- Publication number
- CN107246282A CN107246282A CN201710704365.6A CN201710704365A CN107246282A CN 107246282 A CN107246282 A CN 107246282A CN 201710704365 A CN201710704365 A CN 201710704365A CN 107246282 A CN107246282 A CN 107246282A
- Authority
- CN
- China
- Prior art keywords
- pull bar
- disc
- rotor
- conical profile
- gas turbine
- 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
- F01D5/02—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
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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
- F01D5/028—Blade-carrying members, e.g. rotors the rotor disc being formed of sheet laminae
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
Abstract
The present invention relates to a kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine.This disc of conical profile structure is main by 1, generator terminal of calming the anger rotor, and 2, circumferential pull bar, 3, combustion chamber, 4, circumferential pull bar, 5, moment of torsion sleeve, 6, turbine end rotor, 7, the parts such as circumferential pull bar constitute.From gas-turbine combustion chamber 3 by by compressed air with spray into fuel mixed combustion generate high temperature and high pressure gas, the expansion work in turbine end rotor 6, promote turbine end rotor 6 to rotate, drive the superhigh speed of rotor one rotation of whole gas turbine, chemical energy is converted into mechanical energy.Disc of conical profile is used by the combined rotor in gas turbine, rotor can be preferably in the environment of high temperature and high speed, prevent the pretightning force between combined rotor from gradually lacking so that pull bar relaxes, ensure wheel disc rigidity, combined rotor can improve the life-span that gas turbine combines rotor preferably suitable for the operating mode of HTHP high speed.
Description
Technical field
The present invention relates to a kind of rotor structure for gas turbine, more particularly to a kind of gas turbine circumferential pull bar
Disc of conical profile combined rotor structure.
Background technology
Gas turbine is equipped as typical dual-use high-tech large-sized power, with rigidity is big, intensity is high, weight
Gently, start the features such as fast, efficiency is high, power density is big, be widely used in the fields such as aviation, ship, the energy.
At present, gas turbine structure is complicated, and combined rotor is the core of gas turbine overall design, is directly influenced whole
The performance of individual gas turbine and life-span.The structure of combined rotor is mainly made up of pull bar, wheel disc, blade.Circumferential formula composite braces
Rotor is that wheel disc tension is formed by connecting with many peripheral pull bars on Radius by being distributed in wheel disc.Because gas turbine is long
Phase works in the environment of high temperature hostile, and the combined rotor at especially turbine end is even more to subject high temperature and at a high speed rotation generation
Pretightning force between huge internal stress, combined rotor is gradually lacked so that pull bar relaxation, causes wheel disc rigidly attenuating, cause combustion gas wheel
Machine breaks down.
Therefore, how to solve combined rotor pull bar due to caused by crackle, fatigue, creep equivalent damage combined rotor performance move back
Change is a technical barrier urgently to be resolved hurrily.
The content of the invention
In order to solve turbine engine failure caused by the relaxation of combined rotor pull bar, the present invention provides a kind of week of gas turbine
To the disc of conical profile combined rotor structure of pull bar.The technical solution adopted for the present invention to solve the technical problems is：To combustion gas wheel
The wedge structure alignment of disc of conical profile is pressed on one by wheel disk using circumferential formula pull bar disc of conical profile structure by applying power
Rise, it is ensured that interference fit, prevent relaxation, realize the requirement such as centering, centering of wheel disc.It is uniform on the same Radius of disc of conical profile
Several diameter identical pull bars, the problems such as preventing the bias of wheel disc.
The beneficial effects of the invention are as follows be transferred to the stress concentration point on combined rotor by pull bar same on disc of conical profile
When, the possibility that wheel disc is rigidly reduced caused by being relaxed due to pull bar is reduced, and wheel disc is more compressed in operation process, rigidity
Obtain lifting by a small margin.Due to using disc of conical profile structure, i.e., end face tooth structure need not be processed on wheel disc, is reduced
Manufacture difficulty and expense.
Compared with existing plane wheel disc, plane wheel disc mainly causes wheel disc closely to connect by pull bar pretightning force, wheel disc
Rigidity depend on pull bar.Disc of conical profile then causes wheel disc just to be combined closely when installation by pyramidal structure, and
And in the case where running at high speed, wheel disc combination can become even closer.Divide the big stress born of pull bar equally wheel disc
Taper surface on, reduce and occur because pull bar crackle, pretightning force such as reduce at the turbine engine failure caused by failure.Pass through taper cone pulley
Dish structure prevents the pretightning force between combined rotor from gradually lacking so that pull bar relaxes, it is ensured that wheel disc rigidity, improves gas turbine group
Close the life-span of rotor.
Brief description of the drawings
The present invention is further described with reference to the accompanying drawings and examples.
Fig. 1 is the disc of conical profile combined rotor structure schematic diagram of the circumferential pull bar of gas turbine of the present invention.
Fig. 2 is the local connection diagram of gas turbine disc of conical profile of the present invention.
Fig. 3 is one of disc of conical profile structural representation of the gas turbine of the present invention.
Mark 1, air end of booster rotor in figure, 2, circumferential pull bar, 3, combustion chamber, 4, circumferential pull bar, 5, moment of torsion sleeve, 6, turbine
Hold rotor, 7, circumferential pull bar.
Embodiment
Below in conjunction with the accompanying drawings and the present invention is described in further detail by embodiment, it is to the present invention to implement below
Explanation and the invention is not limited in following examples.The disc of conical profile structure of circumference pull bar of the invention is used for gas turbine,
Therefore specific embodiment is illustrated with a kind of gas turbine：The disc of conical profile structure of circumferential pull bar is main by disc of conical profile,
The parts such as pull bar are constituted.
Gas turbine as shown in Figure 1 wheel discs at different levels use disc of conical profile, pyramidal structure and drawing by disc of conical profile
Wheel disc is closely linked by bar pretightning force so that the connection of gas turbine wheel discs at different levels is integral, it is ensured that the intensity of structure with
And it is complete.Air end of booster rotor 1 realizes the centering and centering of structure by pyramidal structure and torsion pass pin connection.Circumferential pull bar 2 is passed through
Air end of booster rotor 1 and combustion chamber 3 apply the pretightning forces of formed objects by air end of booster with several diameter identical holes on Radius
Rotor 1 links together with combustion chamber 3.It is distributed on combustion chamber 3 by circumferential pull bar 4 on several same Radius of combustion chamber 3
Apply pretightning force with moment of torsion sleeve 5 to be closely joined together.Turbine end rotor 6 is disc of conical profile, moment of torsion sleeve 5 and turbine end
All connected between the most prime wheel disc and turbine end rotor 6 of rotor 6 by pyramidal structure, realize the centering and centering of structure.
Pretightning force is applied with diameter identical hole on several same Radius of turbine end rotor 6 through moment of torsion sleeve 5 by circumferential pull bar 7
It is closely connected integral.
From gas-turbine combustion chamber 3 by by compressed air with spray into fuel mixed combustion generate HTHP gas
Body, the expansion work in turbine end rotor 6 promotes turbine end rotor 6 to rotate, drives the superhigh speed of rotor one of whole gas turbine
Rotation, mechanical energy is converted into by chemical energy.
The pull bar number of described gas turbine combination rotor is no less than 6.
Furthermore, it is necessary to illustrate, described by patent of the present invention is preferred embodiment, but is not limited thereto implementation
Example.Shape, named title of its parts and components etc. can be different, and the content described in this specification is only special to the present invention
Sharp example explanation.It is all to conceive the equivalence changes that described construction, feature and principle is done according to patent of the present invention,
Within the protection domain for being included in patent of the present invention.The person skilled of this area, easily according to examples detailed above, neck
Can patent of the present invention spirit, and make each change of different amplifications, but structure without departing from patent of the present invention or
Surmount scope defined in the claims, all in the protection domain of patent of the present invention.
Claims (8)
1. a kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine, this disc of conical profile architectural feature is：Combustion gas wheel
The wheel discs at different levels of machine all use disc of conical profile, and wheel disc is combined closely by the pyramidal structure and pull bar pretightning force of disc of conical profile
Together so that gas turbine wheel disc connections at different levels are integral.
2. a kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine according to claim 1, it is characterized in that：
Air end of booster rotor 1 realizes the centering and centering of structure by pyramidal structure and torsion pass pin connection.
3. a kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine according to claim 1, it is characterized in that：
Moment of torsion sleeve 5 is connected with turbine end rotor 6 by pyramidal structure, realizes the centering and centering of structure.
4. a kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine according to claim 1, it is characterized in that：
Wheel disc between turbine end rotor 6 all crosses pyramidal structure connection, realizes the centering and centering of structure.
5. a kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine according to claim 2, it is characterized in that：
By circumferential pull bar 2 through air end of booster rotor 1 and the diameter identical tie rod hole on several same Radius on combustion chamber 3, apply
The pretightning force of formed objects links together air end of booster rotor 1 and air end of booster rotor 1 with combustion chamber 3.
6. a kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine according to claim 1, it is characterized in that：
By circumferential pull bar 4 through combustion chamber 3 and the diameter identical hole on several same Radius on moment of torsion sleeve 5, apply identical big
Small pretightning force links together combustion chamber 3 with moment of torsion sleeve 5.
7. a kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine according to claim 3 claim 4,
It is characterized in that：Moment of torsion sleeve 5 and the diameter identical on several same Radius of turbine end rotor 6 are passed through by circumferential pull bar 7
Tie rod hole closely connects it integral.
8. a kind of disc of conical profile combination of the circumferential pull bar of gas turbine according to claim 5 to any one of claim 7
Rotor structure, it is characterized in that：Uniform several diameter identical pull bars realize disc of conical profile on the same Radius of disc of conical profile
Centering, centering etc. require that and circumferential pull bar 2, circumferential pull bar 4, circumferential pull bar 7 is no less than 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710704365.6A CN107246282A (en) | 2017-08-17 | 2017-08-17 | A kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710704365.6A CN107246282A (en) | 2017-08-17 | 2017-08-17 | A kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107246282A true CN107246282A (en) | 2017-10-13 |
Family
ID=60013182
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710704365.6A Pending CN107246282A (en) | 2017-08-17 | 2017-08-17 | A kind of disc of conical profile combined rotor structure of the circumferential pull bar of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107246282A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110821883A (en) * | 2019-12-04 | 2020-02-21 | 哈尔滨电气股份有限公司 | Modularized compressor rotor applied to heavy gas turbine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4123199A (en) * | 1976-03-31 | 1978-10-31 | Tokyo Shibaura Electric Co., Ltd. | Rotor-shaft assembly |
| JPS57193701A (en) * | 1981-05-25 | 1982-11-29 | Hitachi Ltd | Stacked rotor |
| JPS60209603A (en) * | 1984-04-02 | 1985-10-22 | Hitachi Ltd | Rotor of turbo-machine |
| US20030007827A1 (en) * | 2001-07-06 | 2003-01-09 | Peter Broadhead | Coupling arrangement |
-
2017
- 2017-08-17 CN CN201710704365.6A patent/CN107246282A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4123199A (en) * | 1976-03-31 | 1978-10-31 | Tokyo Shibaura Electric Co., Ltd. | Rotor-shaft assembly |
| JPS57193701A (en) * | 1981-05-25 | 1982-11-29 | Hitachi Ltd | Stacked rotor |
| JPS60209603A (en) * | 1984-04-02 | 1985-10-22 | Hitachi Ltd | Rotor of turbo-machine |
| US20030007827A1 (en) * | 2001-07-06 | 2003-01-09 | Peter Broadhead | Coupling arrangement |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110821883A (en) * | 2019-12-04 | 2020-02-21 | 哈尔滨电气股份有限公司 | Modularized compressor rotor applied to heavy gas turbine |
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Application publication date: 20171013 |