CN102116201A - Disc-type rod fastening rotor structure for heavy-duty gas turbine - Google Patents
Disc-type rod fastening rotor structure for heavy-duty gas turbine Download PDFInfo
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- CN102116201A CN102116201A CN2011100419011A CN201110041901A CN102116201A CN 102116201 A CN102116201 A CN 102116201A CN 2011100419011 A CN2011100419011 A CN 2011100419011A CN 201110041901 A CN201110041901 A CN 201110041901A CN 102116201 A CN102116201 A CN 102116201A
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Abstract
The invention discloses a disc-type rod fastening rotor structure for a heavy-duty gas turbine, which comprises multistage compressor wheel discs in a compressor section, wherein the compressor wheel discs are connected and the compressor wheel discs and a middle combustion chamber section are connected through axial twist transmission pins; all stages of compressor wheel discs and the middle combustion chamber section are connected into a whole through central draw rods; the middle combustion section is connected with multistage turbine wheel discs in a turbine section; all stages of turbine wheel discs and the middle combustion chamber section are connected into a whole through prestressed circumferential draw rods; all stages of turbine wheel discs are engaged and the turbine wheel discs and the middle combustion chamber section are engaged through face teeth; therefore, the coaxiality of all stages of compressor wheel discs and the middle combustion chamber section and the coaxiality of all stages of turbine wheel discs and the middle combustion chamber section are guaranteed so as to guarantee the integral centrality of a rotor. The structure has the advantages of high centrality and high assembling efficiency.
Description
Technical field
The present invention relates to the rotor technology field of heavy gas turbine, relate in particular to a kind of disc type rod fastening rotor structure that is used for heavy duty gas turbine.
Background technique
The disc type rod fastening rotor is a kind of very important rotor form, be widely used in large rotating machinery such as the heavy gas turbine, the disc type rod fastening rotor can roughly be divided into gas compressor section, intermediate combustion chamber section and turbine section three parts, the gas compressor section generally has wheel disc more than ten grades, the turbine section generally has wheel disc more than three grades, these wheel discs assemble with various forms by the pretension pull bar, thereby constitute the disc type rod fastening rotor.Practice finds, this rotor that assembles not as the common such easy control each several part of unitary rotor to neutrality, thereby directly influence the dynamic balancing of rotor, efficiency of assembling is low simultaneously.
Summary of the invention
In order to overcome the shortcoming of above-mentioned prior art, the object of the present invention is to provide a kind of disc type rod fastening rotor structure that is used for heavy duty gas turbine, it has the advantage good to neutrality, that efficiency of assembling is high.
To achieve these goals, the technological scheme taked of the present invention is:
A kind of disc type rod fastening rotor structure that is used for heavy gas turbine, comprise the compressor disk 1 of gas compressor section more than 10 grades or 10 grades, connect by axial torsion pass pin 2 between the compressor disk 1, one end of the compressor disk 1 of afterbody and intermediate combustion chamber section 3 is connected by axial torsion pass pin 2, center pull rod 4 is passed the center hole of compressor disks 1 at different levels and intermediate combustion chamber section 3, by pretension center pull rod 4 gas compressor section compressor disks 1 at different levels and intermediate combustion chamber section 3 are connected into integral body, the other end of intermediate combustion chamber section 3 is connected with the turbine wheel disc 5 of turbine section more than 2 grades or 2 grades, turbine section turbine wheel discs 5 at different levels and intermediate combustion chamber section 3 all have 6 holes that are no less than of circumferential distribution, turbine section turbine wheel discs 5 at different levels and intermediate combustion chamber section 3 connect into integral body by the circumferential pull bar 6 of pretension, being 7 engagements of end face tooth between the turbine wheel discs 5 at different levels, is 7 engagements of end face tooth between first order turbine wheel disc 5 and the intermediate combustion chamber section 3.
Be not more than the Spielpassung of 0.005mm between the center hole of described gas compressor section compressor disks 1 at different levels and the center pull rod 4 for radius.
Working principle of the present invention:
Gas compressor section compressor disks 1 at different levels and intermediate combustion chamber section 3 form a whole by center pull rod 4, so just guarantee the coaxality of gas compressor section compressor disks 1 at different levels and intermediate combustion chamber section 3 easily, and between the turbine section turbine wheel discs 5 at different levels, mesh by end face tooth 7 between first order turbine wheel disc 5 and the intermediate combustion chamber section 3, end face tooth 7 has high-precision self contering characteristic, so just guaranteed the coaxality of turbine section turbine wheel discs 5 at different levels and intermediate combustion chamber section 3, gas compressor section and turbine section can both keep good coaxality with intermediate combustion chamber section 3, promptly guaranteed rotor integral body to neutrality.
Because gas compressor section of the present invention has adopted center pull rod, makes efficiency of assembling be higher than circumferential rod fastening rotor; Because turbine section of the present invention has adopted the end face toothing, end face tooth accuracy of alignment and repeatability are all very high, thereby need not dynamic balancing once more after the dismounting, and be therefore good to neutrality, the efficiency of assembling height.
Description of drawings
Fig. 1 is a structural representation of the present invention.
Fig. 2 is the connection diagram of the torsion pass pin 2 of the present invention and the wheel disc 1 of calming the anger.
Embodiment
Below in conjunction with accompanying drawing this bright structural principle and working principle is described in further detail.
See figures.1.and.2, a kind of disc type rod fastening rotor structure that is used for heavy gas turbine, comprise the compressor disk 1 of gas compressor section more than 10 grades or 10 grades, connect by axial torsion pass pin 2 between the compressor disk 1, one end of the compressor disk 1 of afterbody and intermediate combustion chamber section 3 is connected by axial torsion pass pin 2, center pull rod 4 is passed the center hole of compressor disks 1 at different levels and intermediate combustion chamber section 3, by pretension center pull rod 4 and center pull rod nut 8 gas compressor section compressor disks 1 at different levels and intermediate combustion chamber section 3 are connected into integral body, the other end of intermediate combustion chamber section 3 is connected with the turbine wheel disc 5 of turbine section more than 2 grades or 2 grades, turbine section turbine wheel discs 5 at different levels and intermediate combustion chamber section 3 all have 6 holes that are no less than of circumferential distribution, turbine section turbine wheel discs 5 at different levels and intermediate combustion chamber section 3 connect into integral body by circumferential pull bar 6 of pretension and circumferential pull-rod nut 9, being 7 engagements of end face tooth between the turbine wheel discs 5 at different levels, is 7 engagements of end face tooth between first order turbine wheel disc 5 and the intermediate combustion chamber section 3.
Be not more than the 0.005mm Spielpassung for radius between the center hole of described gas compressor section compressor disks 1 at different levels and the center pull rod 4.
Working principle of the present invention:
Gas compressor section compressor disks 1 at different levels and intermediate combustion chamber section 3 form a whole by center pull rod 4, so just guarantee the coaxality of gas compressor section compressor disks 1 at different levels and intermediate combustion chamber section 3 easily, and between the turbine section turbine wheel discs 5 at different levels, mesh by end face tooth 7 between first order turbine wheel disc 5 and the intermediate combustion chamber section 3, end face tooth 7 has high-precision self contering characteristic, so just guaranteed the coaxality of turbine section turbine wheel discs 5 at different levels and intermediate combustion chamber section 3, gas compressor section and turbine section can both keep good coaxality with intermediate combustion chamber section 3, promptly guaranteed rotor integral body to neutrality.
In the accompanying drawing: 1 is compressor disk; 2 are the torsion pass pin; 3 is intermediate combustion chamber section; 4 is center pull rod; 5 is the turbine wheel disc; 6 is circumferential pull bar; 7 is the end face tooth; 8 is the center pull rod nut; 9 is circumferential pull-rod nut.
Claims (2)
1. disc type rod fastening rotor structure that is used for heavy gas turbine, it is characterized in that: comprise the compressor disk (1) of gas compressor section more than 10 grades or 10 grades, connect by axial torsion pass pin (2) between the compressor disk (1), one end of compressor disk of afterbody (1) and intermediate combustion chamber section (3) is connected by axial torsion pass pin (2), center pull rod (4) is passed the center hole of compressor disks at different levels (1) and intermediate combustion chamber section (3), by pretension center pull rod (4) gas compressor section compressor disks at different levels (1) and intermediate combustion chamber section (3) are connected into integral body, the other end of intermediate combustion chamber section (3) is connected with the turbine wheel disc (5) of turbine section more than 2 grades or 2 grades, turbine section turbine wheel discs at different levels (5) and intermediate combustion chamber section (3) all have 6 holes that are no less than of circumferential distribution, turbine section turbine wheel discs at different levels (5) and intermediate combustion chamber section (3) connect into integral body by the circumferential pull bar of pretension (6), being end face tooth (7) engagement between the turbine wheel discs at different levels (5), is end face tooth (7) engagement between first order turbine wheel disc (5) and the intermediate combustion chamber section (3).
2. a kind of disc type rod fastening rotor structure that is used for heavy gas turbine according to claim 1 is characterized in that: the Spielpassung that is not more than 0.005mm between the center hole of described gas compressor section compressor disks at different levels (1) and the center pull rod (4) for radius.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100419011A CN102116201A (en) | 2011-02-22 | 2011-02-22 | Disc-type rod fastening rotor structure for heavy-duty gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100419011A CN102116201A (en) | 2011-02-22 | 2011-02-22 | Disc-type rod fastening rotor structure for heavy-duty gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102116201A true CN102116201A (en) | 2011-07-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011100419011A Pending CN102116201A (en) | 2011-02-22 | 2011-02-22 | Disc-type rod fastening rotor structure for heavy-duty gas turbine |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102359396A (en) * | 2011-07-08 | 2012-02-22 | 西安交通大学 | Disc type rod fastening rotor structure with circumferential tension rod at turbine section for heavy gas turbine |
| CN102691576A (en) * | 2012-06-14 | 2012-09-26 | 中国科学院工程热物理研究所 | Power transmission mechanism of gas compressor and turbine |
| CN103016080A (en) * | 2012-12-31 | 2013-04-03 | 北京全四维动力科技有限公司 | Multistage steam turbine adopting wheel disc pull rod structure |
| KR101624054B1 (en) | 2014-11-21 | 2016-05-24 | 두산중공업 주식회사 | Gas turbine with a plurality of tie rods and assembling method thoreof |
| CN106121733A (en) * | 2016-08-12 | 2016-11-16 | 上海电气燃气轮机有限公司 | A kind of mixed rotor structure for heavy duty gas turbine and assemble method |
| CN110238645A (en) * | 2019-05-31 | 2019-09-17 | 沈阳透平机械股份有限公司 | A kind of turbine rotor spindle mounted device and method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59215903A (en) * | 1983-05-23 | 1984-12-05 | Toshiba Corp | Turbine rotor |
| CN101852096A (en) * | 2010-05-22 | 2010-10-06 | 东方电气集团东方汽轮机有限公司 | Assembly method of draw bar type rotor disk of gas turbine |
| CN101890699A (en) * | 2010-05-22 | 2010-11-24 | 东方电气集团东方汽轮机有限公司 | Stay bolt adjusting mechanism of gas turbine pull rod type rotor and operating method thereof |
-
2011
- 2011-02-22 CN CN2011100419011A patent/CN102116201A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59215903A (en) * | 1983-05-23 | 1984-12-05 | Toshiba Corp | Turbine rotor |
| CN101852096A (en) * | 2010-05-22 | 2010-10-06 | 东方电气集团东方汽轮机有限公司 | Assembly method of draw bar type rotor disk of gas turbine |
| CN101890699A (en) * | 2010-05-22 | 2010-11-24 | 东方电气集团东方汽轮机有限公司 | Stay bolt adjusting mechanism of gas turbine pull rod type rotor and operating method thereof |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102359396A (en) * | 2011-07-08 | 2012-02-22 | 西安交通大学 | Disc type rod fastening rotor structure with circumferential tension rod at turbine section for heavy gas turbine |
| CN102691576A (en) * | 2012-06-14 | 2012-09-26 | 中国科学院工程热物理研究所 | Power transmission mechanism of gas compressor and turbine |
| CN103016080A (en) * | 2012-12-31 | 2013-04-03 | 北京全四维动力科技有限公司 | Multistage steam turbine adopting wheel disc pull rod structure |
| KR101624054B1 (en) | 2014-11-21 | 2016-05-24 | 두산중공업 주식회사 | Gas turbine with a plurality of tie rods and assembling method thoreof |
| US20160146101A1 (en) * | 2014-11-21 | 2016-05-26 | Doosan Heavy Industries Construction Co., Ltd. | Gas turbine with plurality of tie rods and method of assembling the same |
| CN106194436A (en) * | 2014-11-21 | 2016-12-07 | 斗山重工业株式会社 | There is gas turbine and the assemble method thereof of multiple pull bar |
| US9951687B2 (en) | 2014-11-21 | 2018-04-24 | Doosan Heavy Industries Construction Co., Ltd. | Gas turbine with plurality of tie rods and method of assembling the same |
| CN106194436B (en) * | 2014-11-21 | 2018-12-11 | 斗山重工业株式会社 | Gas turbine and its assemble method with multiple pull rods |
| CN106121733A (en) * | 2016-08-12 | 2016-11-16 | 上海电气燃气轮机有限公司 | A kind of mixed rotor structure for heavy duty gas turbine and assemble method |
| CN110238645A (en) * | 2019-05-31 | 2019-09-17 | 沈阳透平机械股份有限公司 | A kind of turbine rotor spindle mounted device and method |
| CN110238645B (en) * | 2019-05-31 | 2020-07-31 | 沈阳透平机械股份有限公司 | Turbine rotor spindle assembling device and method |
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Application publication date: 20110706 |