JPH0514501U - Fluid machine rotor blades - Google Patents
Fluid machine rotor bladesInfo
- Publication number
- JPH0514501U JPH0514501U JP6081291U JP6081291U JPH0514501U JP H0514501 U JPH0514501 U JP H0514501U JP 6081291 U JP6081291 U JP 6081291U JP 6081291 U JP6081291 U JP 6081291U JP H0514501 U JPH0514501 U JP H0514501U
- Authority
- JP
- Japan
- Prior art keywords
- blade
- hole
- screw
- pin
- head
- 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- Withdrawn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
Abstract
(57)【要約】
【目的】 軸流圧縮機、蒸気タービン等の流体機械の動
翼をすきまのない状態で保持し、かつ、分解、組立の際
に部品を繰り返して使用できるようにする。
【構成】 動翼根底部２とディスク３にまたがって軸方
向穴７を穿設し、該穴径よりも大径の頭８を有し先端部
にねじが切られたねじ穴９′を有する翼止めピン９を穴
７に挿入し、穴径より大径の頭１１を有するねじ１０を
翼止めピン９のねじ穴９′に螺合した。
(57) [Summary] [Purpose] To maintain the blades of fluid machinery such as axial compressors and steam turbines without any clearance, and to enable repeated use of parts during disassembly and assembly. [Structure] An axial hole 7 is bored across a root portion 2 of a blade and a disk 3, and a head 8 having a diameter larger than the hole diameter is provided, and a screw hole 9'threaded at a tip end thereof is provided. The wing stop pin 9 was inserted into the hole 7, and the screw 10 having the head 11 having a diameter larger than the hole diameter was screwed into the screw hole 9 ′ of the wing stop pin 9.
Description
【０００１】[0001]
本考案は、サイドエントリ形の軸流圧縮機、蒸気タービン等の流体機械の動翼 に関する。 The present invention relates to a rotor blade of a fluid machine such as a side entry type axial compressor or a steam turbine.
【０００２】[0002]
図３及び図４に、従来のガスタービン用軸流空気圧縮機動翼翼止め構造を示す 。 3 and 4 show a conventional axial flow air compressor rotor blade stopper structure for a gas turbine.
【０００３】 サイドエントリ形動翼１のダブテール形根底部２には、円周方向に溝４Ａが切 られ、根底部２が側方から挿入されるディスク３には穴４Ｂが穿設されており、 ピン５で穴４Ｂ内のコイルばね６を押圧して動翼が挿入される。ピン５が動翼の 溝４Ａの位置に達すると、同ピン５はばね６で押されて溝４Ａ内に突出し、軸方 向の翼止め措置が講じられる。A groove 4A is circumferentially cut in the dovetail-shaped root 2 of the side-entry rotor blade 1, and a hole 4B is formed in a disk 3 into which the root 2 is laterally inserted. , The pin 5 presses the coil spring 6 in the hole 4B to insert the moving blade. When the pin 5 reaches the position of the groove 4A of the moving blade, the pin 5 is pushed by the spring 6 and protrudes into the groove 4A, so that the blade is stopped in the axial direction.
【０００４】[0004]
前記従来の動翼の翼止め構造では、次の問題点があった。 The conventional blade fixing structure for a moving blade has the following problems.
【０００５】 １．翼を分解取り除くときにはピンを剪断しなければならない。従って分解ご とにピンとばねは消耗品となっている。1. When disassembling and removing the wings, the pins must be sheared. Therefore, the pin and spring are consumable items after each disassembly.
【０００６】 ２．ガスタービン用軸流圧縮機動翼根底部とディスク翼溝との間にはすきまが ある。従ってターニング時翼は重力によって上下に移動する。このためピンは溝 内を摺動し、長時間にわたってターニングを行うと、ピンやピン溝が摩耗する場 合がある。2. There is a clearance between the root of the axial compressor blade for gas turbine and the disk blade groove. Therefore, the wing moves vertically due to gravity during turning. Therefore, the pin slides in the groove, and if turning is performed for a long time, the pin and the pin groove may be worn.
【０００７】 ３．蒸気タービンのインテグラルシュラウド（Integral Shroud)翼では、構造 上、前記の止めピン構造を採用することができない。3. Integral Shroud blades of steam turbines cannot structurally adopt the above-mentioned stop pin structure.
【０００８】 本考案は、前記の問題点を解決することができる風力機械の動翼を提供しよう とするものである。The present invention is intended to provide a moving blade of a wind power machine that can solve the above problems.
【０００９】[0009]
本考案の流体機械の動翼は、動翼根底部とディスクに、両者にまたがって軸方 向穴を穿設し、該穴径よりも大きな頭を有し先端部にねじが切られた翼止めピン を前記穴に挿入し、前記穴径よりも大きな頭を有するねじを翼止めピンの前記ね じ部に螺合した。 A blade of a fluid machine according to the present invention is a blade having a root portion and a disk, and an axial hole extending over both of them, having a head larger than the hole diameter, and having a threaded tip portion. The retaining pin was inserted into the hole, and a screw having a head larger than the hole diameter was screwed into the screw portion of the blade retaining pin.
【００１０】[0010]
動翼は、螺合して一体となった翼止めピンとねじの頭によって動翼根底部とデ ィスクにまたがって穿設された軸方向の穴に止められ、軸方向に抜けることがな い。 The blades are screwed together into one piece, and are fixed in the axial holes drilled across the root of the blade and the disk by means of the blade stopper pin and screw head, and they do not slip out in the axial direction.
【００１１】[0011]
本考案の一実施例を、図１及び図２によって説明する。軸流圧縮機の動翼１の 根底部２とディスク３には、両者にまたがる軸方向の穴７が穿設され、同穴７の 穴径よりも大きな頭８を有し、かつ、先端部にめねじが切られたねじ穴９′をも つ翼止めピン９が穴７に挿入される。ディスクの反対側からは、前記穴径よりも 大きな頭１１を有する小ねじ１０が穴７に挿入され、前記翼止めピン９のねじ穴 ９′にねじ込まれる。 An embodiment of the present invention will be described with reference to FIGS. The root portion 2 and the disk 3 of the rotor 1 of the axial compressor are provided with an axial hole 7 extending over both of them, and have a head 8 larger than the hole diameter of the hole 7 and a tip portion. A wing stop pin 9 having a female hole 9 ′ with a female thread is inserted into the hole 7. From the opposite side of the disc, a machine screw 10 having a head 11 larger than the hole diameter is inserted into the hole 7 and screwed into the screw hole 9 ′ of the wing stop pin 9.
【００１２】 なお、以上のようにして動翼１を取付けた後には、翼止めピン９を互いに連結 する回り止めワイヤ１１等による回り止めが施される。After the moving blade 1 is attached as described above, the rotation preventing wire 11 or the like for connecting the blade fixing pins 9 to each other is used to prevent rotation.
【００１３】 本実施例では、動翼１は、ねじ込まれて互いに一体となった翼止めピン９と小 ねじ１０の頭９，１１によって、動翼１の根底部２とディスク３にまたがる軸方 向の穴７に止められ軸方向に抜けることがなく、動翼１がディスク３によってす き間のない状態で保持される。従って、動翼１はディスク３によって確実に保持 されると共に、翼止めピン９、小ねじ１０と穴７の摩耗を防止することができる 。In this embodiment, the moving blade 1 is axially extended across the root portion 2 of the moving blade 1 and the disk 3 by the blade stopper pin 9 and the heads 9 and 11 of the machine screw 10 screwed together. The rotor blade 1 is held in the facing hole 7 and does not slip off in the axial direction, so that the moving blade 1 is held by the disc 3 in a state of no gap. Therefore, the blade 1 can be securely held by the disk 3, and the blade stopper pin 9, the machine screw 10 and the hole 7 can be prevented from being worn.
【００１４】 また、動翼の分解組立に当っては、小ねじ１０を翼止めピン９から外し、又は 小ねじ１０を翼止めピンにねじ込めばよく、その作業を迅速かつ容易に行なうこ とができると共に、これら部品を繰返して使用することができる。In disassembling and assembling the moving blade, the machine screw 10 may be removed from the blade fixing pin 9 or the machine screw 10 may be screwed into the blade fixing pin, and the work can be performed quickly and easily. In addition, these parts can be used repeatedly.
【００１５】[0015]
本考案は、実用新案登録請求の範囲に記載された構成を具備したことによって 、下記の効果がえられる。 １．分解組立が容易で、翼止め部品を繰返し使用することができる。 ２．従来の動翼におけるように、翼止めピン、ねじ及び動翼根底部とディスクに またがって穿設された軸方向穴の摩耗がなくなる。 ３．動翼根底部とディスクにまたがって穿設された軸方向穴と２つの部品である 翼止めピンとねじで構成され、コストを低廉にすることができる。 ４．蒸気タービンのインテグラルシュラウド翼にも適用することができる。 The present invention has the following effects by having the configuration described in the scope of claims for utility model registration. 1. It is easy to disassemble and assemble, and the wing stopper can be used repeatedly. 2. As in conventional blades, there is no wear of the wing stop pins, screws and axial holes drilled across the blade root and disk. 3. It is composed of an axial hole drilled across the root of the blade and the disk, and two parts, a wing stop pin and a screw, which can reduce the cost. 4. It can also be applied to an integral shroud blade of a steam turbine.
【図１】本考案の一実施例の縦断面図である。FIG. 1 is a vertical sectional view of an embodiment of the present invention.
【図２】同実施例の正面図である。FIG. 2 is a front view of the embodiment.
【図３】従来の動翼翼止め装置の縦断面図である。FIG. 3 is a vertical sectional view of a conventional blade fixing device.
【図４】同従来の動翼翼止め装置の正面図である。FIG. 4 is a front view of the conventional blade fixing device.
１ 動翼 ２ 動翼根底部 ３ ディスク ７ 軸方向の穴 ８ 翼止めピンの頭 ９ 翼止めピン ９′ ねじ穴 １０ 小ねじ １１ 小ねじの頭 1 Blade 2 Blade root 3 Disk 7 Axial hole 8 Blade stop pin head 9 Blade stop pin 9'Screw hole 10 Machine screw 11 Machine screw head
Claims (1)
向穴を穿設し、該穴径よりも大径の頭を有し先端部にね
じが切られた翼止めピンを前記穴に挿入し、前記穴径よ
りも大径の頭を有するねじを翼止めピンの前記ねじ部に
螺合したことを特徴とする流体機械の動翼。1. A blade stopper pin having a head having a diameter larger than the hole diameter and having a threaded tip end is inserted into the hole by straddling the root portion of the blade and the disk. A blade of a fluid machine, wherein a screw having a head with a diameter larger than the hole diameter is screwed into the screw portion of the blade fixing pin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6081291U JPH0514501U (en) | 1991-08-01 | 1991-08-01 | Fluid machine rotor blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6081291U JPH0514501U (en) | 1991-08-01 | 1991-08-01 | Fluid machine rotor blades |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0514501U true JPH0514501U (en) | 1993-02-26 |
Family
ID=13153136
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP6081291U Withdrawn JPH0514501U (en) | 1991-08-01 | 1991-08-01 | Fluid machine rotor blades |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0514501U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011012550A (en) * | 2009-06-30 | 2011-01-20 | Hitachi Ltd | Turbine moving blade and turbine rotor for fixing turbine moving blade |
| WO2015075970A1 (en) | 2013-11-20 | 2015-05-28 | 三菱重工業株式会社 | Turbine rotor assembly, blade stop plate for turbine rotor assembly, and method for assembling blade stop plate |
-
1991
- 1991-08-01 JP JP6081291U patent/JPH0514501U/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011012550A (en) * | 2009-06-30 | 2011-01-20 | Hitachi Ltd | Turbine moving blade and turbine rotor for fixing turbine moving blade |
| WO2015075970A1 (en) | 2013-11-20 | 2015-05-28 | 三菱重工業株式会社 | Turbine rotor assembly, blade stop plate for turbine rotor assembly, and method for assembling blade stop plate |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5420221B2 (en) | Improvement of pitch control ring for stator blade of turbomachine | |
| US7549838B2 (en) | Taking air away from the tips of the rotor wheels of a high pressure compressor in a turbojet | |
| JP5553481B2 (en) | Turbomachine fan | |
| JP6241548B2 (en) | Bearing structure and turbocharger | |
| WO2006004965A3 (en) | Device and method for detachably connecting an impeller to a shaft | |
| NL8500704A (en) | COUPLING FOR GAS PRESSURE PIPES. | |
| JP2006037954A (en) | Securing device of moving blade and method of assembling and disassembling moving blade | |
| WO2015075970A1 (en) | Turbine rotor assembly, blade stop plate for turbine rotor assembly, and method for assembling blade stop plate | |
| CA2637278A1 (en) | Holding structure of fan blade | |
| JPH0514501U (en) | Fluid machine rotor blades | |
| CN109708343B (en) | Electronic expansion valve | |
| US20130322985A1 (en) | Retention assembly including sleeve | |
| US6676380B2 (en) | Turbine blade assembly with pin dampers | |
| CN209394592U (en) | A kind of not damaged provision for disengagement of thin-walled cartridge type bushing | |
| JP2017516069A (en) | Device for positioning an inspection tool | |
| US2857134A (en) | Assembly of blades for turbines and the like | |
| CN209812221U (en) | Screw extracting tool structure | |
| JP7154112B2 (en) | Tools and methods for installing wear liners | |
| WO2019174336A1 (en) | Fan blade support assembly for fan blade, air duct assembly, and air conditioner | |
| US2487330A (en) | Fastening device | |
| JP5067208B2 (en) | Turbocharger | |
| KR20040095669A (en) | Control lever attachment with play compensation for blades with variable setting angles | |
| RU158311U1 (en) | AXIAL FAN BLADE FASTENING ASSEMBLY | |
| CN213381289U (en) | Spanner | |
| CN211589930U (en) | Motor spindle dismounting tool |
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: 19951102 |