CN1129279A - Shock-relieving device used on vane of heat turbine - Google Patents
Shock-relieving device used on vane of heat turbine Download PDFInfo
- Publication number
- CN1129279A CN1129279A CN95116056A CN95116056A CN1129279A CN 1129279 A CN1129279 A CN 1129279A CN 95116056 A CN95116056 A CN 95116056A CN 95116056 A CN95116056 A CN 95116056A CN 1129279 A CN1129279 A CN 1129279A
- Authority
- CN
- China
- Prior art keywords
- damping wire
- perforate
- blade
- heat turbine
- damping
- 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
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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
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The purpose of the present invention is raising the stabilisation of blade with damping wire (4). According to the present invention, the purpose can realize by that radii (6, 6') of the cutout part (5) and the buffer wire (4) in the direction of rotary axial line of the blades (2) are smaller than radii (7, 7') in the radial direction.
Description
The present invention relates to a kind of device of on the blade of heat turbine, reducing to vibrate of being used for.
Decrease the vibration of dangerous blade for damping has fatigue to shake, usually use damping wire.Such damping wire loosely penetrates in the perforate that suitably is provided with of a plurality of adjacent blades, and this damping wire is linked to be a vane group with these blades.When blade rotation, damping wire radial outward under centrifugal action abuts in the perforate, by this to each other unbalanced of the blade in the vane group or cause the vibration of phase shifts to carry out damping.
Known up to now damping wire has circular or along the elliptic cross-section of going into flow path direction, this line passes the correspondingly configured perforate of blade.Yet, in the perforate that forms like this, existing than higher notch stress, this notch stress makes the fatigue of materials of blade, thereby its durability is descended, and is last even may cause fault.
The present invention attempts to avoid all these defectives.The objective of the invention is to improve the stability of the blade that is provided with damping wire of heat turbine.
Purpose of the present invention is achieved by following technical solution, have a damping wire to be arranged on a plurality of adjacent blades in the device in the perforate that suitably forms therein, the radial design that the direction along the spin axis of blade of perforate and damping wire stretches becomes the radially radius of stretching, extension less than perforate and damping wire.Thereby on the height of perforate, the cross sectional area of this blade is greater than the cross sectional area of the blade under the circular damping wire situation of equivalent diameter.Therefore the specified stress of blade with and notch stress all reduced.In addition, by the bigger radius of curvature in the perforate both sides notch factor (Kerbfaktor) has also been reduced, this will cause notch stress further to reduce.So just improved the stability of blade significantly.
Damping wire is designed to oval advantageous particularly.The cross sectional area of such damping wire is less than the cross sectional area of the circular damping wire that constitutes with equivalent diameter.Therefore the centrifugal force of oval damping wire is also less, and this durability to blade also plays favourable influence.
In the accompanying drawings, by means of a turbine blade that has the oval aperture that installs damping wire one embodiment of the present of invention are described.In the drawings:
Fig. 1 is a part sectional view that has the turbine blade of the perforate that installs damping wire of the present invention;
Fig. 2 is the sectional view that amplifies in the high power perforate position, that be in working state of Fig. 1;
Fig. 3 is one and is equivalent to Fig. 2 but has the sectional view of another possible damping wire cross section.
Only illustrating understanding the present invention among the figure is those important parts.For example all other turbine blade does not all illustrate.
The turbine wheel dish 1 of a heat turbine is equipped with a plurality of turbine blades 2.Both have a common axis of rotation line 3 (Fig. 1).A plurality of turbine blades 2 connect into a vane group by a damping wire 4.On each turbine blade 2, be provided with a perforate 5 that is used for holding damping wire 4.
An oval aperture 5 is compared with a corresponding round hole, and the semi major axis 7 of supposition oval aperture is equivalent to the radius of round hole.Clearly, the cross section of oval aperture 5 is less than the cross section of round hole.Thereby on the height of perforate 5, the cross sectional area of this turbine blade 2 is greater than the cross sectional area of the blade under circular damping wire situation, thus the predetermined stress of the turbine blade 2 of the solution of the present invention with and notch stress all advantageously reduced.In addition, because the radius of curvature 9 of perforate 5 both sides is bigger than the radius of curvature of corresponding round hole, notch factor and notch stress 8 have also reduced.
Because the cross sectional area of oval damping wire 4 is less, centrifugal force 10 has also just reduced thereupon, thereby the radial load of turbine blade 2 has also reduced.
Fig. 3 shows the another kind of possible cross-sectional configuration of damping wire 4, and the radius of curvature 9 that increases significantly of the both sides by corresponding aperture 5 can also reach and causes littler notch stress 8.
Claims (2)
1. one kind is used for the device that reduces to vibrate on the blade of heat turbine, in this device, there is a damping wire (4) to be arranged in the perforate (5) that suitably forms on a plurality of adjacent blades, it is characterized in that, the radius (6 that the direction of the spin axis along blade (2) (3) of perforate (5) and damping wire (4) stretches, 6 ') be designed to the radius (7,7 ') that radially stretches less than perforate and damping wire.
2. by the described device of claim 1, it is characterized in that damping wire (4) is designed to ellipse.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEP4436730.9 | 1994-10-14 | ||
| DE4436730A DE4436730A1 (en) | 1994-10-14 | 1994-10-14 | Oscillation damper for blades of thermal flow machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1129279A true CN1129279A (en) | 1996-08-21 |
Family
ID=6530757
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN95116056A Pending CN1129279A (en) | 1994-10-14 | 1995-10-06 | Shock-relieving device used on vane of heat turbine |
Country Status (4)
| Country | Link |
|---|---|
| JP (1) | JPH08177402A (en) |
| KR (1) | KR960014594A (en) |
| CN (1) | CN1129279A (en) |
| DE (1) | DE4436730A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100352307B1 (en) * | 2000-05-04 | 2002-09-11 | 박선용 | Heale fluctuation guiding device of tentative loom by using air cylinder |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1005084B (en) * | 1955-09-27 | 1957-03-28 | Siemens Ag | Binding of turbine blades |
-
1994
- 1994-10-14 DE DE4436730A patent/DE4436730A1/en not_active Withdrawn
-
1995
- 1995-10-06 CN CN95116056A patent/CN1129279A/en active Pending
- 1995-10-11 KR KR1019950034910A patent/KR960014594A/en not_active Application Discontinuation
- 1995-10-13 JP JP7265817A patent/JPH08177402A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| DE4436730A1 (en) | 1996-04-18 |
| KR960014594A (en) | 1996-05-22 |
| JPH08177402A (en) | 1996-07-09 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C06 | Publication | ||
| PB01 | Publication | ||
| C53 | Correction of patent for invention or patent application | ||
| CB02 | Change of applicant information |
Applicant after: Asea Brown Boveri AG Applicant before: ABB Management AG |
|
| COR | Change of bibliographic data |
Free format text: CORRECT: APPLICANT; FROM: ABB MANAGENMENT CO., LTD. TO: ASEA BROWN BOVERI |
|
| C01 | Deemed withdrawal of patent application (patent law 1993) | ||
| WD01 | Invention patent application deemed withdrawn after publication |