JPH0417763Y2 - - Google Patents
Info
- Publication number
- JPH0417763Y2 JPH0417763Y2 JP1985030920U JP3092085U JPH0417763Y2 JP H0417763 Y2 JPH0417763 Y2 JP H0417763Y2 JP 1985030920 U JP1985030920 U JP 1985030920U JP 3092085 U JP3092085 U JP 3092085U JP H0417763 Y2 JPH0417763 Y2 JP H0417763Y2
- Authority
- JP
- Japan
- Prior art keywords
- wing
- blade
- groove
- semicircular
- circular hole
- 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.)
- Expired
Links
- 238000000034 method Methods 0.000 description 2
- 238000002513 implantation Methods 0.000 description 1
Description
【考案の詳細な説明】
産業上の利用分野
本考案は蒸気タービン全般に利用するものであ
る。[Detailed Description of the Invention] Industrial Application Field The present invention is applicable to steam turbines in general.
従来の技術
従来タービンの回転体に翼を固定する方法とし
ては止ピンを使用している。第３ａ図でロータ０
１の外径に設けた翼溝０２の外周に、半円状の溝
０３を設けている。この翼溝０２に植込まれる第
３図ｂの翼０４のプラツトホームの腹面側にも半
円状の溝０５が加工されている。第４図に示すよ
うに半円状の溝０３と半円状の溝０５とが重つて
ひとつの円孔ａを形成する。この円孔ａに止ピン
０６（第３ｃ図）を入れて翼０４が軸方向に動か
ないようにしている。このようにして順次翼を固
定していくが、最後に打込む翼０７は最初の翼０
４と接してしまうので、ここには止ピン０６は挿
入できない。BACKGROUND ART Conventionally, a stop pin is used as a method for fixing blades to a rotating body of a turbine. Rotor 0 in Figure 3a
A semicircular groove 03 is provided on the outer periphery of the blade groove 02 provided on the outer diameter of the blade. A semicircular groove 05 is also machined on the ventral side of the platform of the blade 04 shown in FIG. 3b, which is implanted in the blade groove 02. As shown in FIG. 4, the semicircular groove 03 and the semicircular groove 05 overlap to form one circular hole a. A stop pin 06 (Fig. 3c) is inserted into this circular hole a to prevent the blade 04 from moving in the axial direction. In this way, the wings are fixed one after another, but the last wing 07 to be driven in is the first wing 0.
4, so the stop pin 06 cannot be inserted here.
このため最終翼０７の軸方向の動きを固定する
方法として翼根部の側面に止ねじ０８を設けたり
（第４図、第５ａ図）、最終翼をグループを形成す
るシユラウド０９の中央に位置するようにセツト
している（第５ａ図参照）。 For this reason, as a method of fixing the axial movement of the final blade 07, a set screw 08 is provided on the side surface of the blade root (Figures 4 and 5a), and the final blade is located in the center of the shroud 09 that forms the group. (See Figure 5a).
考案が解決しようとする問題点
上述の従来構成によれば、最終翼を固定するた
めに第４図に示すように各段の間隙ｂが狭い場合
は、止ねじ０８を翼根部にねじ込むことが困難で
ある。又翼根部、翼溝部の強度上好ましくない。
さらに第５ａ図に示すようにシユラウド０９がな
い単翼では軸方向の固定ができない。Problems to be Solved by the Invention According to the conventional configuration described above, when the gap b of each stage is narrow as shown in FIG. 4 to fix the final blade, it is not possible to screw the set screw 08 into the blade root. Have difficulty. In addition, it is unfavorable in terms of strength of the blade root and blade groove.
Furthermore, as shown in FIG. 5a, a single blade without a shroud 09 cannot be fixed in the axial direction.
問題点を解決するための手段
本考案は上記問題点を解決するもので、タービ
ンの回転軸に形成された翼溝に次々に植込まれる
翼を、前記翼溝の外周に形成した半円状の溝と前
記翼のプラツトホームの腹面側に形成した半円状
の溝とが重なつて形成される円孔に止ピンを入れ
て順次翼を固定するようにした、回転軸に翼を固
定する装置において、最初に植込む翼の背面側に
も前記腹面側の溝と同じ半円状の溝と表面よりこ
の溝に通ずるスリツトとを穿設し、この最初翼の
背面側の半円状の溝と前記回転軸の翼溝の外周に
形成した半円状の溝とで形成される円孔に仮設し
た止ピンを、最終翼の植込み後に該最終翼の腹面
側の円孔にずらした後、前記最初翼の背面側の円
孔およびスリツトに挿入して前記止ピンの戻りを
止めるピースを配設して成ることを特徴とする、
回転軸に翼を固定する装置に関するものである。Means for Solving the Problems The present invention solves the above-mentioned problems, and includes blades that are successively implanted in blade grooves formed on the rotating shaft of a turbine, each having a semicircular shape formed on the outer periphery of the blade groove. The blade is fixed to the rotating shaft by inserting a stop pin into a circular hole formed by overlapping the groove of the blade and a semicircular groove formed on the ventral side of the blade platform to fix the blade in sequence. In the device, a semicircular groove similar to the groove on the ventral side and a slit communicating with this groove from the surface are bored on the dorsal side of the wing to be implanted first. After the fixing pin temporarily installed in the circular hole formed by the groove and the semicircular groove formed on the outer periphery of the blade groove of the rotating shaft is moved to the circular hole on the ventral side of the final blade after implantation of the final blade. , further comprising a piece inserted into a circular hole and a slit on the back side of the first wing to prevent the stop pin from returning;
This invention relates to a device for fixing a wing to a rotating shaft.
実施例
本考案を添付図面の第１ａ図ないし第２ｂ図に
例示した好適な実施例により説明する。最初に植
込む翼（すなわち最初翼）および最後に植込む翼
（すなわち最終翼）以外の中間の普通翼は従来例
と同じである。第３ａ図ないし第５ｂ図の従来例
と同じように、回転軸すなわちロータ１の外径上
に翼溝２を全周に設け、翼溝２の外周上に半円状
の溝３を加工する。この翼溝に翼を組立てた時半
円状の溝３は翼の半円状の溝５と重なつて一つの
円孔となる。この円孔に止めピン６を入れて翼を
軸方向に固定するのである。この止ピン６は隣接
翼を組立てることによりプラツトホームで抜ける
のを防いでいる。しかしこのままでは従来例につ
いて前述したように、最後に植込んだ翼すなわち
最終翼には止ピンを入れることができる。DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will now be described with reference to preferred embodiments illustrated in FIGS. 1a to 2b of the accompanying drawings. The intermediate ordinary wings other than the wing to be implanted first (ie, the first wing) and the wing to be implanted last (ie, the last wing) are the same as in the conventional example. Similar to the conventional example shown in FIGS. 3a to 5b, blade grooves 2 are provided all around the outer diameter of the rotor 1, that is, the rotating shaft, and semicircular grooves 3 are machined on the outer periphery of the blade grooves 2. . The half-circular groove 3 in which the blade is assembled into the blade groove overlaps with the semicircular groove 5 of the blade to form one circular hole. A fixing pin 6 is inserted into this circular hole to fix the wing in the axial direction. This stop pin 6 prevents it from coming off on the platform by assembling adjacent wings. However, if this continues, a stop pin can be inserted into the last blade implanted, that is, the last blade, as described above with respect to the conventional example.
本考案では最初翼１０にその腹面側に設けた半
円状の溝５と同じ溝１１を背面側（反対側）に設
ける（第２ａ図参照）。ロータ１の翼溝２の外周
には全周に半円状の溝３が加工されているので、
腹面、背面両方に溝を設けたこの最初翼１０を植
込むと、ふたつの円孔が形成され、これの円孔の
両方に止ピン６を入れることができる。この背面
側の溝１１には表面から延びるスリツト１２を設
ける（第２ｂ図参照）。 In the present invention, the same groove 11 as the semicircular groove 5 provided on the ventral side of the wing 10 is first provided on the back side (opposite side) (see Fig. 2a). Since semicircular grooves 3 are machined around the entire circumference of the blade grooves 2 of the rotor 1,
When this first wing 10, which has grooves on both the ventral and dorsal surfaces, is implanted, two circular holes are formed, and the stop pins 6 can be inserted into both of these circular holes. This groove 11 on the back side is provided with a slit 12 extending from the front surface (see FIG. 2b).
最初翼１０（第１ａ図、第３ａ図参照）を翼溝
２に植込み、円孔に止ピン６を挿入して固定す
る。このように順々に翼（普通翼）を植込んで行
く。最後に最終翼１５を組立てる前に第１ｂ図に
図示の如く最初翼１０の背面側の溝１１と溝３と
が形成する円孔に止ピン６を入れておく。次いで
最終翼１５を組立てた後、スリツト１２からピー
ス１３を差し込んで止ピン６をこじり、これを第
１ｃ図に示すように移動させ、最終翼４の腹面側
の翼５まで挿入セツトする。その後この止ピン６
が戻らないようにスリツト１２および溝１１内に
ピース１３を第１ｃ図に示すように充分に入れ
る。このピース１３が飛び出さないようにスリツ
ト１２の表面部に符号１４で示すようにコーキン
グする（第１ｄ図）。これでピース１３は飛び出
さないし、止ピン６も元の最初翼の円孔に戻るこ
とはない。このようにして最終翼にも普通翼と同
じように腹面側に止ピン６が配設されるのであ
る。 First, the blade 10 (see FIGS. 1a and 3a) is inserted into the blade groove 2 and fixed by inserting the stop pin 6 into the circular hole. In this way, the wings (ordinary wings) are implanted one after another. Finally, before assembling the final blade 15, a stop pin 6 is inserted into the circular hole formed by the groove 11 and the groove 3 on the back side of the blade 10, as shown in FIG. 1b. Next, after assembling the final wing 15, the piece 13 is inserted through the slit 12, the stop pin 6 is pried, and this is moved as shown in FIG. 1c to insert and set the final wing 4 up to the wing 5 on the ventral side. Then this stop pin 6
Place the piece 13 into the slit 12 and groove 11 sufficiently to prevent it from returning as shown in FIG. 1c. To prevent this piece 13 from popping out, caulk the surface of the slit 12 as shown by reference numeral 14 (FIG. 1d). With this, the piece 13 will not fly out, and the stop pin 6 will not return to its original circular hole in the wing. In this way, the stop pin 6 is provided on the ventral surface of the final wing in the same way as the normal wing.
考案の効果
本考案は上記の構成であり、普通翼に挿入した
止ピン構造と最終翼に挿入した止ピン構造とは同
じとなり、最終翼を軸方向に確実に固定できる。
又翼組立後、ピースをコーキングすることにより
ピースはしつかりと固定することができる。これ
は単翼であつても固定できる。又組立作業が迅速
確実に行なえる。Effects of the Invention The present invention has the above configuration, and the stop pin structure inserted into the normal wing and the stop pin structure inserted into the final wing are the same, and the final wing can be securely fixed in the axial direction.
Also, after assembling the wing, the pieces can be firmly fixed by caulking them. This can be fixed even if it is a single wing. Also, assembly work can be done quickly and reliably.
第１ａ図は本考案の好適な実施例の平面図、第
１ｂ図、第１ｃ図はその正面図、第１ｄ図はその
側面図、第１ｅ図はピースの斜視図、第２ａ図は
最初翼の正面図、第２ｂ図は同斜視図、第３ａ図
は本考案及び従来例のロータの斜視図、第３ｂ図
は翼の斜視図、第３ｃ図は止ピン６の斜視図、第
３ｄ図は止ねじの斜視図、第４図はロータに翼を
取付けた側面図、第５ａ図は従来例の正面図、第
５ｂ図は第５ａ図のＡ−Ａ視平面図である。
１……ロータ、２……翼溝、３……溝、５……
腹面側の溝、６……止ピン、１０……最初翼、１
１……背面側の溝、１２……スリツト、１３……
ピース、１４……コーキング、１５……最終翼。
Figure 1a is a plan view of the preferred embodiment of the present invention, Figures 1b and 1c are its front view, Figure 1d is its side view, Figure 1e is a perspective view of the piece, and Figure 2a is the first wing. Figure 2b is a perspective view of the same, Figure 3a is a perspective view of the rotor of the present invention and the conventional example, Figure 3b is a perspective view of the blade, Figure 3c is a perspective view of the stop pin 6, Figure 3d is a perspective view of the same. 5 is a perspective view of the set screw, FIG. 4 is a side view of the blades attached to the rotor, FIG. 5a is a front view of the conventional example, and FIG. 5b is a plan view taken along line AA in FIG. 5a. 1...Rotor, 2...Blade groove, 3...Groove, 5...
Ventral groove, 6...stop pin, 10...first wing, 1
1...Groove on the back side, 12...Slit, 13...
Peace, 14...Caulking, 15...Final wing.
Claims (1)
込まれる翼を、前記翼溝の外周に形成した半円状
の溝と前記翼のプラツトホームの腹面側に形成し
た半円状の溝とが重なつて形成される円孔に止ピ
ンを入れて順次翼を固定するようにした、回転軸
に翼を固定する装置において、最初に植込む翼の
背面側にも前記腹面側の溝と同じ半円状の溝と表
面よりこの溝に通ずるスリツトとを穿設し、この
最初翼の背面側の半円状の溝と前記回転軸の翼溝
の外周に形成した半円状の溝とで形成される円孔
に仮設した止ピンを、最終翼の植込み後に該最終
翼の腹面側の円孔にずらした後、前記最初翼の背
面側の円孔およびスリツトに挿入して前記止ピン
の戻りを止めるピースを配設して成ることを特徴
とする、回転軸に翼を固定する装置。 The blades are successively implanted into blade grooves formed on the rotating shaft of the turbine, with semicircular grooves formed on the outer periphery of the blade grooves and semicircular grooves formed on the ventral side of the platform of the blades. In a device for fixing wings to a rotating shaft, in which the wings are fixed in sequence by inserting pins into circular holes that are formed overlapping each other, the dorsal side of the wing to be implanted first has the same groove as the ventral side. A semicircular groove and a slit communicating with the groove from the surface are bored, and the semicircular groove on the back side of the first blade and the semicircular groove formed on the outer periphery of the blade groove of the rotating shaft are connected to each other. After the final wing is implanted, a stop pin temporarily installed in the circular hole to be formed is moved to the circular hole on the ventral side of the final wing, and then inserted into the circular hole and slit on the back side of the first wing. A device for fixing a wing to a rotating shaft, characterized by having a piece that prevents the wing from returning.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1985030920U JPH0417763Y2 (en) | 1985-03-06 | 1985-03-06 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1985030920U JPH0417763Y2 (en) | 1985-03-06 | 1985-03-06 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS61147302U JPS61147302U (en) | 1986-09-11 |
| JPH0417763Y2 true JPH0417763Y2 (en) | 1992-04-21 |
Family
ID=30531050
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1985030920U Expired JPH0417763Y2 (en) | 1985-03-06 | 1985-03-06 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0417763Y2 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5149831B2 (en) * | 2009-02-12 | 2013-02-20 | 三菱重工コンプレッサ株式会社 | Turbine blade fixed structure and turbine |
| KR101689085B1 (en) * | 2015-08-03 | 2017-01-02 | 두산중공업 주식회사 | Assembly of the bucket with which the fixture and the bucket for a turbine blade |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5482505A (en) * | 1977-12-14 | 1979-06-30 | Hitachi Ltd | Steam turbine |
| JPS5848729A (en) * | 1981-09-16 | 1983-03-22 | Toyota Motor Corp | Method of starting electronically controlled fuel- injection engine |
| JPS5857605A (en) * | 1981-09-30 | 1983-04-05 | Toshiba Anpetsukusu Kk | Digital recorder and reproducer |
-
1985
- 1985-03-06 JP JP1985030920U patent/JPH0417763Y2/ja not_active Expired
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5482505A (en) * | 1977-12-14 | 1979-06-30 | Hitachi Ltd | Steam turbine |
| JPS5848729A (en) * | 1981-09-16 | 1983-03-22 | Toyota Motor Corp | Method of starting electronically controlled fuel- injection engine |
| JPS5857605A (en) * | 1981-09-30 | 1983-04-05 | Toshiba Anpetsukusu Kk | Digital recorder and reproducer |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS61147302U (en) | 1986-09-11 |
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