JPH11294387A - Compressor rotor blade - Google Patents
Compressor rotor bladeInfo
- Publication number
- JPH11294387A JPH11294387A JP9889598A JP9889598A JPH11294387A JP H11294387 A JPH11294387 A JP H11294387A JP 9889598 A JP9889598 A JP 9889598A JP 9889598 A JP9889598 A JP 9889598A JP H11294387 A JPH11294387 A JP H11294387A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- groove
- push
- disk
- compressor rotor
- 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.)
- Withdrawn
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、軸流コンプレッサ
動翼に関し、特に翼根部がディスクの翼溝に挿入されて
固定されている型式のコンプレッサ動翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an axial compressor blade, and more particularly, to a compressor blade having a root portion inserted and fixed in a blade groove of a disk.
【０００２】[0002]
【従来の技術】従来の軸流コンプレッサ動翼は、図７に
示すように、翼部１と翼根部２が一体構造になってお
り、その翼根部２がディスク３に形成された翼溝４に挿
入されている。このように構成されたコンプレッサ動翼
において、回転中には翼に働く遠心力Ｆｂにより翼根部
２とディスク３のコンタクト面５同志が接触し、コンタ
クト面の摩擦力によって翼はディスク３に固定される。2. Description of the Related Art As shown in FIG. 7, a conventional axial-flow compressor blade has a blade portion 1 and a blade root portion 2 which are integrally formed, and the blade root portion 2 has a blade groove 4 formed on a disk 3. Has been inserted. In the compressor blade thus configured, the centrifugal force Fb acting on the blade during rotation causes the blade root portion 2 and the contact surfaces 5 of the disk 3 to contact each other, and the blade is fixed to the disk 3 by the frictional force of the contact surface. You.
【０００３】従来の軸流コンプレッサ動翼における翼の
固定状態は、翼溝４の形状と翼に働く遠心力Ｆｂだけで
決まるため、翼が短く作用する遠心力が小さい場合には
回転中の翼の固定状態が翼毎にばらつき、翼の固有振動
数が大きくばらつくという欠点があった。[0003] The fixed state of the blade in the conventional axial-flow compressor blade is determined only by the shape of the blade groove 4 and the centrifugal force Fb acting on the blade. There is a drawback that the fixed state of the blade varies from blade to blade, and the natural frequency of the blade greatly varies.
【０００４】図８は、軸流コンプレッサ動翼における回
転数に対する翼の振動数を示しているが、図に斜線部分
の上下幅で示されるように翼の振動数には翼毎にばらつ
きが生じていた。[0004] Fig. 8 shows the blade frequency with respect to the rotation speed of the axial-flow compressor rotor blade. As shown by the vertical width of the hatched portion in the figure, the blade frequency varies from blade to blade. I was
【０００５】[0005]
【発明が解決しようとする課題】軸流コンプレッサ動翼
では通常前段静翼のノズルウェーク励振力との共振を回
避させる必要があるが、前記したように固有振動数のば
らつきが大きい場合には共振回避が事実上不可能であり
翼が破損する原因になることがあった。In an axial flow compressor rotor blade, it is usually necessary to avoid resonance with the nozzle wake excitation force of the preceding stage stationary blade. Avoidance was virtually impossible and could cause wing damage.
【０００６】本発明は、ディスクの翼溝内に翼根部を挿
入して固定してなるコンプレッサ動翼において、翼毎の
ばらつきを少く固定可能に構成したコンプレッサ動翼を
提供することを課題としている。SUMMARY OF THE INVENTION It is an object of the present invention to provide a compressor rotor in which a blade root is inserted into and fixed in a blade groove of a disk and which can be fixed with a small variation between blades. .
【０００７】[0007]
【課題を解決するための手段】本発明は、前記課題を解
決するため、コンプレッサ動翼の翼根部を挿入するディ
スクの翼溝の底部に更に所定の深さの溝を形成し、その
溝内に適当な厚さの押上げピースを挿入した構造のコン
プレッサ動翼を提供する。According to the present invention, in order to solve the above-mentioned problems, a groove having a predetermined depth is further formed at the bottom of a blade groove of a disk into which a blade root of a compressor blade is inserted, and the groove is formed in the groove. To provide a compressor rotor blade having a structure in which a push-up piece having an appropriate thickness is inserted into the compressor rotor blade.
【０００８】このように構成した本発明のコンプレッサ
動翼においては、翼溝の底に形成された溝内に挿入され
た押上げピースに回転時に生ずる遠心力が翼溝内に挿入
されている翼根部を押し上げる。[0008] In the compressor rotor blade of the present invention configured as described above, the centrifugal force generated during rotation of the push-up piece inserted into the groove formed at the bottom of the blade groove is inserted into the blade groove. Push up the root.
【０００９】このため、押上げピースに働く遠心力の分
だけ翼根部とディスクのコンタクト面の摩擦力が大きく
なり、ディスクに対するコンプレッサ動翼の固定が剛に
なる。これによって翼の振動数が上昇し、翼毎の振動数
のばらつきも小さくなる。For this reason, the frictional force between the blade root and the contact surface of the disk is increased by the centrifugal force acting on the push-up piece, and the compressor rotor is fixed to the disk rigidly. As a result, the frequency of the blade increases, and the variation in the frequency of each blade also decreases.
【００１０】図６は、本発明のコンプレッサ動翼におけ
るばらつきの小さくなった翼の振動数を示しており、図
６は図８に比較して振動数の変化幅が小さくなってい
る。以上の作用により本発明によるコンプレッサ動翼で
は前段静翼のノズルウェーク励振力等との共振を回避す
ることが可能となる。FIG. 6 shows the frequencies of the blades of the compressor rotor blades of the present invention with reduced variations, and FIG. 6 shows a smaller variation in the frequency than FIG. With the above operation, it is possible to avoid resonance with the nozzle wake excitation force of the preceding stage stationary blade in the compressor rotor blade according to the present invention.
【００１１】また、本発明は前記課題を解決するため、
コンプレッサ動翼の翼根部を挿入するディスクの翼溝の
底部にスペースを設け、そのスペース内にクサビを打ち
込んだ構造のコンプレッサ動翼を提供する。Further, the present invention has been made in order to solve the above-mentioned problems.
Provided is a compressor blade having a structure in which a space is provided at the bottom of a blade groove of a disk into which a blade root of a compressor blade is inserted, and wedges are driven into the space.
【００１２】このように構成した本発明のコンプレッサ
動翼においては、打ち込まれたクサビによる押上力と、
回転時にクサビに働く遠心力によって翼根部を押し上げ
るので、翼根部とディスクの間のコンタクト面の摩擦力
が大きくなり、翼の固定条件が剛になる。[0012] In the compressor rotor blade of the present invention configured as described above, the push-up force due to the driven wedge,
Since the blade root is pushed up by centrifugal force acting on the wedge during rotation, the frictional force of the contact surface between the blade root and the disk increases, and the condition for fixing the blade becomes rigid.
【００１３】前記したようにディスクに取付けられた翼
の振動数が上昇し翼毎の振動数のばらつきが少くなるの
で、前段静翼のノズルウェーク励振力等との共振を回避
することが可能となる。このようにクサビを打ち込んだ
構成を採用すると、小さなクサビを挿入するだけで翼の
振動数の大きさとばらつきを調整することができる。As described above, since the frequency of the blade attached to the disk increases and the variation in the frequency of each blade decreases, it is possible to avoid resonance with the nozzle wake excitation force of the preceding stage stationary blade. Become. By adopting a configuration in which a wedge is driven in this way, it is possible to adjust the magnitude and variation of the vibration frequency of the blade only by inserting a small wedge.
【００１４】[0014]
【発明の実施の形態】以下、本発明によるコンプレッサ
動翼について図１〜図５に示した実施の形態に基づいて
具体的に説明する。なお、以下の実施の形態において、
図７に示した従来の装置と同じ構成の部分には説明を簡
単にするため同じ符号を付してある。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A compressor rotor blade according to the present invention will be specifically described below with reference to the embodiments shown in FIGS. In the following embodiment,
The same components as those of the conventional device shown in FIG. 7 are denoted by the same reference numerals for simplification of description.
【００１５】（第１実施形態）まず、図１〜図３に示す
第１実施形態によるコンプレッサ動翼について説明す
る。図１及び図３に示すように各翼根部２が挿入される
ようにディスク３に設けられた翼溝４の下側（底）に適
当な深さの押上げピース溝６を設け、その溝６の中に押
上げピース７を挿入する。図２に示すように、挿入する
押上げピース７の厚さは、必要とする振動数の変更量に
よって変える。(First Embodiment) First, a compressor rotor blade according to a first embodiment shown in FIGS. 1 to 3 will be described. As shown in FIGS. 1 and 3, a push-up piece groove 6 having an appropriate depth is provided on the lower side (bottom) of the blade groove 4 provided on the disk 3 so that each blade root 2 is inserted. The push-up piece 7 is inserted into 6. As shown in FIG. 2, the thickness of the push-up piece 7 to be inserted changes according to the required change amount of the frequency.
【００１６】また押上げピース溝６は、図３に示すよう
に運転中の押上げピースの脱落を防ぐためストッパ９を
設けた構造にし、押上げピース７を高圧側から挿入し低
圧側まで完全に貫通させなくてもよい。このように押上
げピース溝６を高圧側から低圧側まで貫通させない構造
とすることにより空気の漏れを防止する利点が生ずる。The push-up piece groove 6 has a structure in which a stopper 9 is provided to prevent the push-up piece from dropping off during operation as shown in FIG. 3, and the push-up piece 7 is inserted from the high pressure side to the low pressure side. It does not have to be penetrated. The structure in which the push-up piece groove 6 is not penetrated from the high pressure side to the low pressure side has an advantage of preventing air leakage.
【００１７】第１実施形態のコンプレッサ動翼は以上の
構成を有しており、押上げピース溝６の中に適当な厚さ
の押上げピース７を挿入すると、回転時には、翼の遠心
力Ｆｂに加え図１に示すように押上げピースに働く遠心
力Ｆｐの分だけ翼根部２とディスク３のコンタクト面５
の摩擦力が大きくなり、翼の固定条件が剛になるため振
動数が上昇し、翼毎の振動数のばらつきも小さくなる。The compressor rotor blade of the first embodiment has the above-described configuration. When the push-up piece 7 having an appropriate thickness is inserted into the push-up piece groove 6, the centrifugal force Fb In addition, as shown in FIG. 1, the contact surface 5 of the blade root portion 2 and the disk 3 is equivalent to the centrifugal force Fp acting on the lifting piece.
The frictional force of the blade increases, and the blade fixing condition becomes rigid, so that the frequency increases, and the variation in the frequency of each blade also decreases.
【００１８】すなわち、もともと図８に示すように広い
範囲でばらついていた振動数を図６に示すようにほとん
どばらつきをなくすることができる。従って、本実施形
態のコンプレッサ動翼は、前段静翼のノズルウェーク励
振力等との共振を確実に回避することができるため、信
頼性を向上させることができる。That is, as shown in FIG. 6, it is possible to substantially eliminate the variation of the frequency which originally varied in a wide range as shown in FIG. Therefore, the compressor rotor blade of the present embodiment can reliably avoid resonance with the nozzle wake excitation force or the like of the preceding stage stationary blade, thereby improving reliability.
【００１９】（第２実施形態）次に、図４、図５に示す
第２実施形態によるコンプレッサ動翼について説明す
る。図４において、ディスク３に設けられた翼溝４内に
は、各翼の翼根部２が挿入されるが、この翼溝４は翼根
部２の厚さよりも深くされており、挿入された翼根部２
の下方にはスペースが生ずるようになっている。(Second Embodiment) Next, a compressor blade according to a second embodiment shown in FIGS. 4 and 5 will be described. In FIG. 4, the blade roots 2 of the respective blades are inserted into the blade grooves 4 provided on the disk 3, and the blade grooves 4 are made deeper than the thickness of the blade roots 2. Root 2
There is a space below the space.
【００２０】翼根部２の下方に形成されたスペース内に
はクサビ８が挿入される。クサビ８を翼根部２とディス
ク３の間に挿入したのち、適当な強さで打ち込んで、翼
根部２を押し上げる。A wedge 8 is inserted into a space formed below the blade root 2. After inserting the wedge 8 between the blade root 2 and the disk 3, the wedge 8 is driven in with appropriate strength to push up the blade root 2.
【００２１】クサビ８を挿入するスペース（溝）は上流
側から下流側まで貫通させても良いが、クサビの押し上
げ力が弱くクサビの脱落の心配がある場合は図３で説明
したと同じように低圧側まで貫通させないような溝形状
にしておけばよい。The space (groove) into which the wedge 8 is inserted may be penetrated from the upstream side to the downstream side. However, if the wedge push-up force is weak and there is a concern that the wedge may fall off, as described with reference to FIG. The groove may be formed so as not to penetrate to the low pressure side.
【００２２】以上説明したように、本第２実施形態のコ
ンプレッサ動翼のように翼根とディスクの間にクサビ８
を打ち込んで翼を押し上げると、回転時には、翼の遠心
力Ｆｂに加え、図４に示すようにクサビ８に働く遠心力
Ｆｐとクサビ８の押上力Ｆｗの分だけ翼根部２とディス
ク３のコンタクト面５の摩擦力が大きくなり、翼の固定
条件が剛になる。As described above, the wedge 8 is located between the blade root and the disk like the compressor rotor blade of the second embodiment.
When the wing is pushed up to rotate, the contact between the blade root portion 2 and the disk 3 by the centrifugal force Fp acting on the wedge 8 and the pushing force Fw of the wedge 8 as shown in FIG. The frictional force on the surface 5 increases, and the conditions for fixing the wing become rigid.
【００２３】この結果、先に説明した第１実施形態の場
合と同様に振動数が上昇し、翼毎の振動数のばらつきも
小さくなる。従って、前段静翼のノズルウェーク励振力
等との共振を確実に回避させることができるため信頼性
を向上させることができる。As a result, the frequency increases as in the case of the first embodiment described above, and the variation in the frequency among the blades also decreases. Therefore, resonance with the nozzle wake excitation force of the preceding stage stationary blade can be reliably avoided, so that the reliability can be improved.
【００２４】また、この場合はクサビ効果によって生じ
る押上力も利用しているため、クサビ８として小さな部
材を挿入するだけで翼の振動数の大きさとばらつきを調
整することができる。なお、クサビ８の押上力は、クサ
ビ８のテーパ角度と打ち込み量を適当に選ぶことにより
調整することができる。Further, in this case, since the push-up force generated by the wedge effect is also used, the magnitude and variation of the blade frequency can be adjusted only by inserting a small member as the wedge 8. The pushing force of the wedge 8 can be adjusted by appropriately selecting the taper angle of the wedge 8 and the driving amount.
【００２５】[0025]
【発明の効果】以上説明したように、本発明は翼根部を
挿入して固定するためのディスクの翼溝の底部に溝を形
成し、その溝内に押上げピースを挿入したコンプレッサ
動翼を提供する。As described above, the present invention provides a compressor blade having a groove formed at the bottom of a blade groove of a disk for inserting and fixing a blade root portion, and a push-up piece inserted into the groove. provide.
【００２６】このように構成した本発明のコンプレッサ
動翼においては、回転時に押上げピースの遠心力の分だ
け翼根部とディスクのコンタクト面の摩擦力が大きくな
り固定条件が剛になるため振動数が上昇し、翼毎の振動
数のばらつきも小さくなる。In the compressor rotor blade of the present invention configured as described above, the frictional force between the blade root portion and the contact surface of the disk is increased by the centrifugal force of the push-up piece during rotation, and the fixing condition becomes rigid. And the variation in the frequency of each blade is reduced.
【００２７】また、本発明は、ディスクの翼溝の底部に
スペースを設け、そのスペース内にクサビを打ち込んだ
構造のコンプレッサ動翼を提供する。The present invention also provides a compressor blade having a structure in which a space is provided at the bottom of a blade groove of a disk and wedges are driven into the space.
【００２８】このように構成した本発明のコンプレッサ
動翼においては、クサビを適当な強さで打ち込んで翼根
を押し上げておくと、回転時にはクサビに働く遠心力と
クサビの押上力の分だけ翼根部とディスク部のコンタク
ト面の摩擦力が大きくなり、翼の固定条件が剛になる。In the compressor rotor blade of the present invention configured as described above, when a wedge is driven with an appropriate strength and the blade root is pushed up, the centrifugal force acting on the wedge during rotation and the pushing force of the wedge are increased. The frictional force between the contact surface of the root portion and the disk portion increases, and the condition for fixing the wing becomes rigid.
【００２９】以上のように、本発明のコンプレッサ動翼
では翼の振動数が上昇し、翼毎の振動数のばらつきも小
さくなるため、前段静翼のノズルウェーク励振力等との
共振を確実に回避させることができる。As described above, in the compressor rotor blade of the present invention, the vibration frequency of the blades increases and the variation in the vibration frequency of each blade also decreases, so that resonance with the nozzle wake excitation force of the preceding stage stationary blade is ensured. Can be avoided.
【図１】本発明の第１実施形態によるコンプレッサ動翼
の構造を示す説明図。FIG. 1 is an explanatory diagram showing a structure of a compressor rotor blade according to a first embodiment of the present invention.
【図２】本発明の第１実施形態によるコンプレッサ動翼
における翼根部に対する押上げピースの組合せ態様を示
す説明図。FIG. 2 is an explanatory diagram showing a combination of a push-up piece and a blade root in a compressor rotor blade according to the first embodiment of the present invention.
【図３】本発明の第１実施形態によるコンプレッサ動翼
における押上げピース溝の形成状態を示す説明図。FIG. 3 is an explanatory view showing a state in which a lifting piece groove is formed in the compressor rotor blade according to the first embodiment of the present invention.
【図４】本発明の第２実施形態によるコンプレッサ動翼
の構造を示す説明図。FIG. 4 is an explanatory view showing a structure of a compressor rotor blade according to a second embodiment of the present invention.
【図５】本発明の第２実施形態によるコンプレッサ動翼
における翼根部に対するクサビの組合せ状態を示す説明
図。FIG. 5 is an explanatory diagram showing a combination state of wedges on a blade root portion in a compressor rotor blade according to a second embodiment of the present invention.
【図６】本発明のコンプレッサ動翼における翼の振動数
のばらつき状態を示す線図。FIG. 6 is a diagram showing a variation state of a blade vibration frequency in a compressor rotor blade of the present invention.
【図７】従来のコンプレッサ動翼の構造を示す説明図。FIG. 7 is an explanatory view showing the structure of a conventional compressor rotor blade.
【図８】従来のコンプレッサ動翼における翼の振動数の
ばらつき状態を示す線図。FIG. 8 is a diagram showing a variation state of blade frequency in a conventional compressor rotor blade.
１ 翼部 ２ 翼根部 ３ ディスク ４ 翼溝 ５ コンタクト面 ６ 押上げピース溝 ７ 押上げピース ８ クサビ Ｆｂ 翼の遠心力 Ｆｐ ピースの遠心力 Ｆｗ クサビの押上げ力 DESCRIPTION OF SYMBOLS 1 Wing part 2 Wing root part 3 Disk 4 Wing groove 5 Contact surface 6 Push-up piece groove 7 Push-up piece 8 Wedge Fb Centrifugal force of wing Fp Centrifugal force of piece Fw Push-up force of wedge
Claims (2)
挿入して翼を固定したコンプレッサ動翼において、前記
翼溝の底部に溝を形成し、同溝内に押上げピースを挿入
したことを特徴とするコンプレッサ動翼。1. A compressor blade in which a blade root is inserted into a blade groove formed in a disk to fix the blade, a groove is formed at the bottom of the blade groove, and a push-up piece is inserted into the groove. A compressor rotor blade characterized in that:
挿入して翼を固定したコンプレッサ動翼において、前記
翼溝の底部にスペースを設け、同スペース内にクサビを
打ち込んでなることを特徴とするコンプレッサ動翼。2. A compressor blade in which a blade root is inserted into a blade groove formed in a disk to fix the blade, a space is provided at the bottom of the blade groove, and a wedge is driven into the space. Features compressor blades.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9889598A JPH11294387A (en) | 1998-04-10 | 1998-04-10 | Compressor rotor blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9889598A JPH11294387A (en) | 1998-04-10 | 1998-04-10 | Compressor rotor blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH11294387A true JPH11294387A (en) | 1999-10-26 |
Family
ID=14231875
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP9889598A Withdrawn JPH11294387A (en) | 1998-04-10 | 1998-04-10 | Compressor rotor blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH11294387A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006275032A (en) * | 2005-03-30 | 2006-10-12 | Hitachi Ltd | Turbine moving blade and turbine facility using same |
| JP2007298036A (en) * | 2006-04-27 | 2007-11-15 | Snecma | System for holding blade of rotor |
| JP2008184927A (en) * | 2007-01-29 | 2008-08-14 | Edwards Kk | Vacuum pump |
| JP2010007536A (en) * | 2008-06-26 | 2010-01-14 | Hitachi Ltd | Turbine moving blade fixing structure |
| JP2014125047A (en) * | 2012-12-26 | 2014-07-07 | Kawasaki Heavy Ind Ltd | Propeller blade fixing mechanism |
-
1998
- 1998-04-10 JP JP9889598A patent/JPH11294387A/en not_active Withdrawn
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006275032A (en) * | 2005-03-30 | 2006-10-12 | Hitachi Ltd | Turbine moving blade and turbine facility using same |
| JP4498964B2 (en) * | 2005-03-30 | 2010-07-07 | 株式会社日立製作所 | Turbine blade and turbine equipment using the same |
| JP2007298036A (en) * | 2006-04-27 | 2007-11-15 | Snecma | System for holding blade of rotor |
| JP2008184927A (en) * | 2007-01-29 | 2008-08-14 | Edwards Kk | Vacuum pump |
| JP2010007536A (en) * | 2008-06-26 | 2010-01-14 | Hitachi Ltd | Turbine moving blade fixing structure |
| JP2014125047A (en) * | 2012-12-26 | 2014-07-07 | Kawasaki Heavy Ind Ltd | Propeller blade fixing mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Withdrawal of application because of no request for examination |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 20050705 |