CN103850715A - Rotor wheel disc - Google Patents
Rotor wheel disc Download PDFInfo
- Publication number
- CN103850715A CN103850715A CN201210506805.4A CN201210506805A CN103850715A CN 103850715 A CN103850715 A CN 103850715A CN 201210506805 A CN201210506805 A CN 201210506805A CN 103850715 A CN103850715 A CN 103850715A
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- China
- Prior art keywords
- rotor disk
- blade root
- recess
- blade
- wheel disc
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Abstract
The invention provides a rotor wheel disc applied to gas turbines and steam turbines. The rotor wheel disc comprises blade root grooves for accommodating blades. Each blade root groove is provided with a recessed portion on one high-stiffness side of the rotor wheel disc. Each recessed portion is used for balancing the stiffness of the rotor wheel disc on two sides of the corresponding blade root groove, so that the blades accommodated in the blade root grooves do not incline due to different stiffness of the two sides of the blade root grooves. Through the recessed portions cut in the blade root grooves, the technical problem of unbalanced stiffness of the rotor wheel disc on two sides of the blades is solved. The recessed portions are simple and easy to process, the stiffness of rotor wheel disc portions on two sides of the blades can be balanced, and stress generated on the rotor wheel disc can be reduced.
Description
Technical field
The present invention relates to gas turbine and steam turbine field, relate in particular to the rotor disk of gas turbine and steam turbine.
Background technique
As shown in Figure 1, the rotor assembly of steam turbine and gas turbine comprises rotor disk and multiple rotor blade.In the time of work, working fluid can enter from the front side of rotor disk (Upstream), and flows out from the rear side (downstream) of rotor disk.Rotor disk is provided with the blade root slot for holding blade root.When steam turbine and gas turbine work, blade need to rotate in the environment high speed of High Temperature High Pressure.In this case, the easy run-off the straight of blade, blade lean is steam turbine and very distinct issues of gas turbine field at present.Blade lean can affect air flow path, and gap between blade tip and cylinder.This finally can affect the efficiency of steam turbine and gas turbine, also may cause blade wear simultaneously.
Summary of the invention
The rigidity imbalance of the rotor disk part that it is blade root slot front side and rear side that claimant's process research discovery causes with a main cause of the rotor disk blade lean of two row or multi-row blade.The object of the invention is the rigidity of balance blade root slot front side and rear side rotor disk part, reduce or prevent blade lean, to reduce the wearing and tearing of blade, extend the life-span of blade, improve the working efficiency of gas turbine or steam turbine.
Design concept of the present invention is: reduce the rigidity of this side rotor disk by making blade root slot have recess in larger rotor disk one side of rigidity, thereby make the rigidity of this side rotor disk of blade root slot and the rigidity balance of an other side rotor disk.
Particularly, one embodiment of the present of invention provide a kind of rotor disk for gas-turbine, it comprises the blade root slot that holds blade, wherein, described blade root slot is provided with recess in the larger side of rotor disk rigidity, described recess is for the rigidity of balance blade root slot both sides rotor disk, thereby the blade that makes to be contained in described blade root slot can not tilt because the rigidity of the rotor disk of blade root slot both sides is different.
Above-described embodiment has overcome the unbalanced technical problem of blade both sides rotor disk rigidity by cut recess in blade root slot.Operation is simple for recesses machined, and rigidity that can balance blade both sides rotor disk part also can reduce the stress producing on rotor disk simultaneously.
Preferably, described recess runs through described blade root slot along the circumferencial direction of rotor disk.The recess that runs through blade root slot more easily and blade root slot machine simultaneously, the while also makes vaned inclination improve simultaneously.
Preferably, the side that recess stretches into rotor disk has lead angle.The stress that lead angle can reduce to produce on recess, the life-span of Extending Rotor wheel disc.
Preferably, blade root slot is the T-shaped groove arranging along the circumferencial direction of rotor disk.On axial (being the thickness direction of wheel disc, the namely major axes orientation of gas turbine and steam turbine) of described rotor disk, be provided with many row's blade root slots.This makes, on a rotor disk, multiple blade rows to be set, and can make gas-turbine increase work efficiency.
Preferably, recess is rectangle or wedge shape.The recess of rectangle and wedge shape can make the stress increase on rotor disk less in reducing rotating disk one side rigidity.
Can find out from description above, in an embodiment of the present invention, by recess being set at blade root slot in the larger side of the rotor disk part rigidity of its both sides (front side or rear side), rigidity that can balance blade root slot both sides rotor disk part, thereby can reduce or prevent blade lean, to reduce the wearing and tearing of blade, improve the life-span of blade and the working efficiency of steam turbine and gas turbine.
Accompanying drawing explanation
Further feature of the present invention, feature, advantage and benefit will become more apparent by the detailed description below in conjunction with accompanying drawing.Wherein:
Fig. 1 illustrates existing a kind of vaned rotor disk of installing;
Fig. 2 illustrates the perspective view that the rotor disk of two row's blades is installed in one embodiment of the invention;
Fig. 3 illustrates the sectional view of above-described embodiment rotor wheel rim A-A face;
Fig. 4 has listed the simulation result that uses embodiment of the present invention rotor wheeling disk structure.
Embodiment
In accompanying drawing, the reference character of all parts is as follows: rotor disk 1, blade 2, blade root slot 3, rotor disk part 4 and 5, recess 6, recess lead angle 51.
As shown in Figures 2 and 3, blade 2 is fixed on rotor disk 1 by blade root slot 3.Blade root slot is the T-shaped groove processing along the circumferencial direction rotary cutting of rotor disk.Blade root slot 3 is provided with recess 6 in the larger side of rotor disk rigidity, and recess 6 can run through blade root slot 3 on the circumferencial direction of rotor disk.Can use Tool in Cutting to process recess 6, tool sharpening easily operates, and processing cost is low.Recess 6 runs through that blade root slot 3 makes recess more easily and blade root slot machines simultaneously, and vaned inclination is improved simultaneously.
The following describes position how to choose recess 6, shape, the degree of depth and area.About the position of recess 6, first, recess 6 will be arranged on the position that can not cause rotor disk gas leakage.Because rotor disk part 4,5 is provided with stator blade, for preventing gas leakage, (being the direction of gas turbine or steam turbine main shaft) preferably vertically, but not radial cutting recess 6.Meanwhile, because need to extending in blade root slot, cutter processes recess 6, so the position of recess 6 need to conveniently process.Meanwhile, the shape of recess preferably can reduce rigidity to greatest extent, makes stress increase minimum simultaneously, for example, can select rectangle, wedge shape or semicircle.The degree of depth of recess depends primarily on the ability of processing, if recess too deeply easily causes cracking of cutter.The size of the rigidity that the area of recess should be adjusted is as required determined.The mode of area that can be by increasing gradually recess obtains the suitable area of recess.For example, for a kind of blade of particular type, can first cut a recess that area is little, then go out radial displacement poor of the surface of contact left and right sides of blade root and blade root slot 3 by numerical simulation calculation, and then continue to cut, increase the area of recess, go out again radial displacement poor of the surface of contact left and right sides of blade root and blade root slot 3 by numerical simulation calculation, by constantly increasing the area of recess and such numerical simulation calculation repeatedly, finally make the area of the difference minimum of radial displacement be the area of the recess of the blade that is suitable for this type.
In order to reduce the stress of recess 6, the side preferably extending in rotor disk part 4,5 at institute's recess 6 arranges lead angle 51.Lead angle should be tried one's best greatly, to reduce to greatest extent the stress of recess 6.The turbine rotor wheel disc rigidity that multiple blade rows is set in the axial direction of rotor disk is easily uneven, so the above-mentioned blade root slot structure with recess arranges on the rotor disk of many row's blade root slots on being preferred for axially in the embodiment of the present invention.
In Fig. 4, having listed on a kind of gas-turbine compressor of SIEMENS's design uses the disclosed rotor disk of embodiments of the invention as the 5th and the 6th grade, (what in figure, from left to right illustrate is followed successively by the 5th with the simulation result of the 7th and the 8th grade of rotor disk, the six, seven and the experimental value of the 8th grade of rotor disk).Wherein, the degree of depth of the 5th and the 6th grade of rotor disk left side recess is 25mm, and lead angle radius is 8mm, and width is 16mm, and the degree of depth of right side recess is 18mm, and lead angle radius is 8mm, and width is 16mm; The degree of depth of the seven or eight grade of rotor disk left side recess is 15mm, and lead angle radius is 7mm, and width is 14mm; The degree of depth 10mm of right side recess, width is 10mm, lead angle radius is 5mm.Arrange after above-mentioned recess, the inclination that the inclination of the 5th grade blade has reduced by 60%, the 6 grade blade has reduced by 38%.Arrange after recess the 7th and the inclination of the 8th grade blade also reduced.
Although the application of rotor disk of the present invention on gas turbine has just been described above, it will be appreciated by those skilled in the art that this rotor disk can also be applied on steam turbine and other similar equipment.Meanwhile, above disclosed each embodiment of the present invention can make various modification and change essential in the situation that not departing from invention, these modification and change and all should fall within protection scope of the present invention within.Therefore, protection scope of the present invention should be limited by appending claims.
Claims (6)
1. a rotor disk (1), it comprises the blade root slot (3) that holds blade (2), wherein, described blade root slot (3) is provided with recess (6) in the larger side of rotor disk rigidity, described recess (6) is for the rigidity of balance blade root slot (3) both sides rotor disk, thereby the blade (2) that makes to be contained in described blade root slot can not tilt because the rigidity of the rotor disk of blade root slot both sides is different.
2. rotor disk as claimed in claim 1, wherein said recess (6) runs through described blade root slot (3) on the circumferencial direction of rotor disk (1).
3. rotor disk as claimed in claim 2, wherein said recess (6) has lead angle (51) at the side that stretches into rotor disk.
4. rotor disk as described in claim 1, wherein said blade root slot (3) is T-shaped groove.
5. rotor disk as described in claim 1 is wherein provided with many row's blade root slots (3) in the axial direction of described rotor disk (1).
6. rotor disk as claimed in claim 1, wherein said recess (6) is rectangle or wedge shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210506805.4A CN103850715A (en) | 2012-11-30 | 2012-11-30 | Rotor wheel disc |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210506805.4A CN103850715A (en) | 2012-11-30 | 2012-11-30 | Rotor wheel disc |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103850715A true CN103850715A (en) | 2014-06-11 |
Family
ID=50858809
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210506805.4A Pending CN103850715A (en) | 2012-11-30 | 2012-11-30 | Rotor wheel disc |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103850715A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104863894A (en) * | 2015-04-30 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas compressor wheel disk and rotor |
| EP3059389A1 (en) * | 2015-02-17 | 2016-08-24 | Rolls-Royce plc | Gas turbine rotor disc with assymetric circumferential slot |
| CN113915163A (en) * | 2021-10-12 | 2022-01-11 | 浙江意动科技股份有限公司 | Compressor rotor blade connection structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0478234A1 (en) * | 1990-09-27 | 1992-04-01 | General Electric Company | Stress-relieved rotor blade attachment slot |
| EP1048821A2 (en) * | 1999-04-30 | 2000-11-02 | General Electric Company | Stress relieved blade root |
| EP1703080A1 (en) * | 2005-03-03 | 2006-09-20 | ALSTOM Technology Ltd | Rotating machine |
| EP2055897A1 (en) * | 2008-04-23 | 2009-05-06 | ALSTOM Technology Ltd | Flexible Shims |
| CN102121400A (en) * | 2009-11-10 | 2011-07-13 | 阿尔斯托姆科技有限公司 | Rotor for an axial-throughflow turbomachine and moving blade for such a rotor |
-
2012
- 2012-11-30 CN CN201210506805.4A patent/CN103850715A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0478234A1 (en) * | 1990-09-27 | 1992-04-01 | General Electric Company | Stress-relieved rotor blade attachment slot |
| EP1048821A2 (en) * | 1999-04-30 | 2000-11-02 | General Electric Company | Stress relieved blade root |
| EP1703080A1 (en) * | 2005-03-03 | 2006-09-20 | ALSTOM Technology Ltd | Rotating machine |
| EP2055897A1 (en) * | 2008-04-23 | 2009-05-06 | ALSTOM Technology Ltd | Flexible Shims |
| CN102121400A (en) * | 2009-11-10 | 2011-07-13 | 阿尔斯托姆科技有限公司 | Rotor for an axial-throughflow turbomachine and moving blade for such a rotor |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3059389A1 (en) * | 2015-02-17 | 2016-08-24 | Rolls-Royce plc | Gas turbine rotor disc with assymetric circumferential slot |
| US10001134B2 (en) | 2015-02-17 | 2018-06-19 | Rolls-Royce Plc | Rotor disc |
| CN104863894A (en) * | 2015-04-30 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas compressor wheel disk and rotor |
| CN104863894B (en) * | 2015-04-30 | 2018-03-20 | 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 compressor disk and rotor |
| CN113915163A (en) * | 2021-10-12 | 2022-01-11 | 浙江意动科技股份有限公司 | Compressor rotor blade connection structure |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140611 |