JPH06212905A - Fixed blade in moving blade cascade - Google Patents
Fixed blade in moving blade cascadeInfo
- Publication number
- JPH06212905A JPH06212905A JP629193A JP629193A JPH06212905A JP H06212905 A JPH06212905 A JP H06212905A JP 629193 A JP629193 A JP 629193A JP 629193 A JP629193 A JP 629193A JP H06212905 A JPH06212905 A JP H06212905A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- rotor
- fixed
- fixed blade
- fixing
- 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
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【0001】[0001]
【産業上の利用分野】本発明は、蒸気タービンのロータ
に動翼の環状翼列をなす動翼翼列を形成するために、ロ
ータに設けられ、動翼を挿入する切欠溝に位置する動翼
翼列の固定翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention is directed to a rotor blade of a steam turbine, which is provided in a rotor for forming a rotor blade row forming an annular blade row of rotor blades and is located in a notch groove into which the rotor blade is inserted. Regarding fixed wing of a row.
【0002】[0002]
【従来の技術】蒸気タービンはロータに環状翼列をなし
て植込まれた動翼と、ロータを囲むケーシングに環状翼
列をなして植込まれた静翼とが翼段落を形成し、蒸気が
この翼段落を流れることによりロータを回転させて仕事
をする。ところで、動翼の環状翼列をなす動翼翼列は、
次記のようにして形成される。ロータに設けられた環状
の翼溝に連通し、外部から動翼の脚部を挿入可能にロー
タに設けられた切欠溝に動翼を順次挿入し、この切欠溝
から前記環状の翼溝に動翼の脚部を挿入して環状翼列を
形成する。ここで、環状翼列を形成する最後の動翼は切
欠溝の位置で固定翼としてロータに固定手段により固定
され、環状翼列をなす動翼翼列が形成される。2. Description of the Related Art In a steam turbine, moving blades which are implanted in a rotor in an annular blade row and stationary blades which are implanted in a casing surrounding the rotor in an annular blade row form a blade stage, and a steam turbine is formed. Works by rotating the rotor by flowing through this wing paragraph. By the way, the rotor blade row forming the annular blade row of rotor blades is
It is formed as described below. Communicating with the annular blade groove provided in the rotor, the rotor blades are sequentially inserted into the notch groove provided in the rotor so that the legs of the blade can be inserted from the outside, and the rotor blade moves from the notch groove to the annular blade groove. The legs of the wings are inserted to form an annular cascade. Here, the final moving blade forming the annular blade row is fixed to the rotor as a fixed blade at the position of the notch groove by the fixing means, and the moving blade blade row forming the annular blade row is formed.
【0003】図5は上記の固定翼が配設された動翼の環
状翼列をなす動翼翼列の部分平面図(図6のA矢視
図)、図6は図5のB−B部分断面図である。図5,図
6において動翼1は翼部2と脚部3とからなり、脚部3
をロータ4に設けられた切欠溝からこれに連通する翼溝
に順次挿入してかしめ片5を介して環状に並べ、切欠溝
に翼部6と脚部7とからなる固定翼8を配して動翼の環
状翼列をなす動翼翼列を形成している。なお固定翼8は
脚部7の周囲の動翼1の脚部3に接する箇所では斜めに
打込まれる固定ピン10で、一方ロータ4に接する箇所
では固定ねじ11によりロータ4に固定されている。FIG. 5 is a partial plan view of a rotor blade row forming an annular blade row of the rotor blades on which the above fixed blades are arranged (a view from the arrow A in FIG. 6), and FIG. 6 is a portion BB in FIG. FIG. In FIGS. 5 and 6, the moving blade 1 is composed of a blade portion 2 and a leg portion 3, and the leg portion 3
Are sequentially inserted from the notch groove provided in the rotor 4 into the blade groove that communicates with the rotor 4, and are arranged in an annular shape through the caulking piece 5, and the fixed blade 8 including the blade portion 6 and the leg portion 7 is arranged in the notch groove. Form a rotor blade cascade forming an annular blade cascade of rotor blades. The fixed blade 8 is fixed to the rotor 4 around the leg 7 by a fixing pin 10 which is driven obliquely at a position in contact with the leg 3 of the moving blade 1, and at a position in contact with the rotor 4 by a fixing screw 11 at a position in contact with the rotor 4. .
【0004】このような構成により、固定翼8は固定ピ
ン10,固定ねじ11により固定されているので、ロー
タ4が回転してもその遠心力により固定翼8は抜け落ち
ない。With this structure, the fixed blade 8 is fixed by the fixing pin 10 and the fixing screw 11, so that even if the rotor 4 rotates, the fixed blade 8 does not fall out due to the centrifugal force.
【0005】[0005]
【発明が解決しようとする課題】従来の固定翼の構造で
は、ロータの回転時の遠心力により抜け落ちないように
するために、固定ピンや固定ねじの固定部品の本数を多
くしたり、固定部品の大きさを大きくする必要があると
いう欠点がある。本発明の目的は、固定翼を固定する固
定部品からなる固定構造を簡略化することのできる動翼
翼列の固定翼を提供することである。In the structure of the conventional fixed blade, in order to prevent the rotor from coming off due to centrifugal force during rotation of the rotor, the number of fixing parts such as fixing pins and fixing screws is increased, and the fixing parts are fixed. There is a drawback that it is necessary to increase the size of. An object of the present invention is to provide a fixed blade of a moving blade cascade that can simplify a fixing structure including a fixed component that fixes the fixed blade.
【0006】[0006]
【課題を解決するための手段】上記課題を解決するため
に、本発明によれば動翼の脚部を蒸気タービンのロータ
に設けられた切欠溝からこの溝に続く環状の翼溝に順次
挿入して動翼を環状に配し、切欠溝に位置してロータに
固定手段により固定される動翼翼列の固定翼において、
固定翼にロータの回転時生じる遠心力を軽減する軽減手
段を設けるものとする。In order to solve the above-mentioned problems, according to the present invention, the legs of the moving blade are sequentially inserted from the notch groove provided in the rotor of the steam turbine into the annular blade groove following this groove. Then, the rotor blades are annularly arranged, and the rotor blades are arranged in the notch groove and fixed to the rotor by the fixing means.
The fixed blade shall be provided with a reducing means for reducing the centrifugal force generated when the rotor rotates.
【0007】上記の軽減手段は固定翼の脚部に孔を設け
るものとする。The above-mentioned reducing means is provided with holes in the leg portions of the fixed wing.
【0008】[0008]
【作用】ロータに設けられた環状の翼溝に連通し、動翼
の脚部を挿入する切欠溝に位置する固定翼にロータの回
転による遠心力を軽減する軽減手段を設けること、この
手段として固定翼の脚部に孔を設けることにより、固定
翼の重量は低減するので、固定翼がうける遠心力は小さ
くなる。したがって固定翼を固定する固定部品を少なく
する等の固定構造を簡略化することができる。The fixed blade, which communicates with the annular blade groove provided in the rotor and is located in the notch groove into which the leg portion of the moving blade is inserted, is provided with a reducing means for reducing the centrifugal force due to the rotation of the rotor. By providing the holes in the legs of the fixed blade, the weight of the fixed blade is reduced, so that the centrifugal force received by the fixed blade is reduced. Therefore, it is possible to simplify the fixing structure such as reducing the number of fixing parts for fixing the fixed blades.
【0009】[0009]
【実施例】以下図面に基づいて本発明の実施例について
説明する。図1は本発明の実施例による固定翼が固定さ
れて植込まれたロータの部分断面図(図2のD−D部分
断面図)、図2は図1のC矢視による固定翼を備える動
翼翼列の部分平面図である。なお、図1,図2において
図5,図6の従来例と同一部品には同じ符号を付し、そ
の説明を省略する。図1,図2において従来例と異なる
のは固定翼8の脚部7に円周方向に貫通する長孔12を
設けて重量を低減し、固定翼8を脚部7の両側で固定ね
じ11のみでロータ4に固定したことである。Embodiments of the present invention will be described below with reference to the drawings. 1 is a partial cross-sectional view of a rotor according to an embodiment of the present invention in which fixed blades are fixed and implanted (partial cross-sectional view taken along the line D-D of FIG. 2), and FIG. It is a partial top view of a moving blade cascade. 1 and 2, the same parts as those of the conventional example of FIGS. 5 and 6 are designated by the same reference numerals, and the description thereof will be omitted. 1 and 2 are different from the conventional example in that the leg portion 7 of the fixed blade 8 is provided with an elongated hole 12 penetrating in the circumferential direction to reduce the weight, and the fixed blade 8 is fixed on both sides of the leg portion 7 with fixing screws 11 It is fixed to the rotor 4 only by itself.
【0010】このような構成により、固定翼8を脚部7
の両側でロータ4に固定ねじ11のみで固定しても、ロ
ータ4の回転による遠心力は軽減しているので、この遠
心力により固定翼8は抜け落ちない。図3は本発明の異
なる実施例による固定翼が固定されて植込まれたロータ
の部分断面図(図4のF−F部分断面図)、図4は図3
のE矢視による固定翼を備える動翼翼列の部分平面図で
ある。図3,図4において固定翼8の脚部7に円周方向
に貫通する丸孔14,15を設けた他は図1,図2に示
すものと同じである。With such a structure, the fixed wing 8 is connected to the leg 7
Even if the rotor 4 is fixed to the rotor 4 on both sides with only the fixing screw 11, the centrifugal force due to the rotation of the rotor 4 is reduced, so that the stationary blade 8 does not fall out by this centrifugal force. FIG. 3 is a partial cross-sectional view of a rotor in which fixed blades are fixed and implanted according to another embodiment of the present invention (F-F partial cross-sectional view of FIG. 4), and FIG.
FIG. 7 is a partial plan view of a rotor blade cascade including fixed blades as viewed from the arrow E of FIG. 3 and 4, it is the same as that shown in FIGS. 1 and 2, except that the leg portions 7 of the fixed blade 8 are provided with circular holes 14 and 15 penetrating in the circumferential direction.
【0011】このような構成により、固定翼8を前述の
ように固定ねじ11により固定することにより、前述と
同じ効果が得られる。With this structure, the same effect as described above can be obtained by fixing the fixed blade 8 with the fixing screw 11 as described above.
【0012】[0012]
【発明の効果】以上の説明から明らかなように、本発明
によれば固定翼に遠心力を軽減する軽減手段、この手段
として固定翼の脚部に孔を設けたことにより、固定翼の
重量が低減するので、ロータの回転による遠心力が低減
し、このため固定部品の本数を少なくしたり、小さくす
ることができ、固定構造を簡略化することができる。As is apparent from the above description, according to the present invention, the weight of the fixed blade is reduced by providing the fixed blade with a reducing means for reducing the centrifugal force. Since the centrifugal force due to the rotation of the rotor is reduced, the number of fixing parts can be reduced or reduced, and the fixing structure can be simplified.
【図1】本発明の実施例による固定翼が固定されて植込
まれたロータの図2に示す図のD−D部分断面図FIG. 1 is a partial cross-sectional view taken along the line DD of FIG. 2 showing a rotor with fixed blades fixedly implanted according to an embodiment of the present invention.
【図2】図1のC矢視による固定翼を備える動翼翼列の
部分平面図FIG. 2 is a partial plan view of a rotor blade row including fixed blades as viewed from the direction of arrow C in FIG.
【図3】本発明の異なる実施例による固定翼が固定され
て植込まれたロータの図4に示す図のF−F部分断面図FIG. 3 is a partial cross-sectional view taken along line F-F of FIG. 4 showing a rotor with fixed blades fixedly implanted according to a different embodiment of the present invention.
【図4】図3のE矢視による固定翼を備える動翼翼列の
部分平面図FIG. 4 is a partial plan view of a rotor blade cascade including fixed blades as viewed from the direction of arrow E in FIG.
【図5】従来の固定翼を備える動翼翼列の図6に示す図
のA矢視による部分平面図FIG. 5 is a partial plan view of a rotor blade row including a conventional fixed blade as viewed in the direction of arrow A in the diagram shown in FIG.
【図6】図5のB−B部分断面図6 is a partial cross-sectional view taken along the line BB of FIG.
1 動翼 2 翼部 3 脚部 6 翼部 7 脚部 8 固定翼 11 固定ねじ 12 長孔 14 丸孔 15 丸孔 1 Moving Blade 2 Wing Part 3 Leg Part 6 Wing Part 7 Leg Part 8 Fixed Wing 11 Fixing Screw 12 Long Hole 14 Round Hole 15 Round Hole
Claims (2)
られた切欠溝からこの溝に続く環状の翼溝に順次挿入し
て動翼を環状に配し、切欠溝に位置してロータに固定手
段により固定される動翼翼列の固定翼において、固定翼
にロータの回転時生じる遠心力を軽減する軽減手段を設
けたことを特徴とする動翼翼列の固定翼。Claim: What is claimed is: 1. A rotor blade is arranged in a notch groove by inserting the leg portions of the rotor blade from a notch groove provided in a rotor of a steam turbine into an annular blade groove following the groove in order. A fixed blade of a moving blade cascade fixed to a fixed blade of the moving blade cascade, wherein the fixed blade is provided with a reducing means for reducing a centrifugal force generated when the rotor rotates.
は、固定翼の脚部に孔を設けたことを特徴とする動翼翼
列の固定翼。2. The fixed blade of a moving blade cascade according to claim 1, wherein the reducing means has holes in the legs of the fixed blade.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP629193A JPH06212905A (en) | 1993-01-19 | 1993-01-19 | Fixed blade in moving blade cascade |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP629193A JPH06212905A (en) | 1993-01-19 | 1993-01-19 | Fixed blade in moving blade cascade |
Publications (1)
Publication Number | Publication Date |
---|---|
JPH06212905A true JPH06212905A (en) | 1994-08-02 |
Family
ID=11634286
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP629193A Pending JPH06212905A (en) | 1993-01-19 | 1993-01-19 | Fixed blade in moving blade cascade |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH06212905A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR100936566B1 (en) * | 2003-11-25 | 2010-01-13 | 제너럴 일렉트릭 캄파니 | Method of installing stationary blades of a turbine and turbine structure having a radial loading pin |
JP2015086876A (en) * | 2013-10-31 | 2015-05-07 | ゼネラル・エレクトリック・カンパニイ | Methods and systems for securing turbine nozzles |
EP2873808A1 (en) * | 2013-11-19 | 2015-05-20 | MTU Aero Engines GmbH | Rotor-blade group, method and flow engine |
-
1993
- 1993-01-19 JP JP629193A patent/JPH06212905A/en active Pending
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR100936566B1 (en) * | 2003-11-25 | 2010-01-13 | 제너럴 일렉트릭 캄파니 | Method of installing stationary blades of a turbine and turbine structure having a radial loading pin |
JP2015086876A (en) * | 2013-10-31 | 2015-05-07 | ゼネラル・エレクトリック・カンパニイ | Methods and systems for securing turbine nozzles |
EP2873808A1 (en) * | 2013-11-19 | 2015-05-20 | MTU Aero Engines GmbH | Rotor-blade group, method and flow engine |
US10041363B2 (en) | 2013-11-19 | 2018-08-07 | MTU Aero Engines AG | Blade-disk assembly, method and turbomachine |
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