JPS61205303A - Stopper in axial direction for turbine moving blade - Google Patents
Stopper in axial direction for turbine moving bladeInfo
- Publication number
- JPS61205303A JPS61205303A JP4269085A JP4269085A JPS61205303A JP S61205303 A JPS61205303 A JP S61205303A JP 4269085 A JP4269085 A JP 4269085A JP 4269085 A JP4269085 A JP 4269085A JP S61205303 A JPS61205303 A JP S61205303A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- seal plate
- cooling air
- stopper
- leaf spring
- 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
【発明の詳細な説明】 産業上の利用分野 この発明は、タービン動翼の軸方向翼止装置に関する。[Detailed description of the invention] Industrial applications The present invention relates to an axial blade stop device for turbine rotor blades.
従来の技術
タービン動翼の翼止装置のうち、半径方向翼止装置には
、従来からクリスマスツリ一方式が採用されているが、
いま、空気冷却式ガスタービン動翼を挙例して説述する
と、第５図において、翼グラットフオーム部２の外方に
ガス流れ１４中に暴露される翼プロフィル部１を突設さ
せるとともに、一部を後述する翼単にその軸方向に圧入
させることによって、該動翼に負荷される大違心力ＩＣ
耐えさせており、しかも大きな問題もなくて一般に使用
されている。なお、同図において、前記翼プラットフォ
ーム部の後流側端の翼車同局方向の下側に後述する冷却
空気シール板端を嵌入させる冷却空気シール板翼側挿入
溝５を削設している。Conventional technology Among the blade stop devices for turbine rotor blades, the Christmas tree type has traditionally been adopted for the radial blade stop device.
Now, to explain an air-cooled gas turbine rotor blade as an example, in FIG. A large eccentric force IC is applied to the rotor blade by simply press-fitting a portion of the blade in the axial direction of the blade, which will be described later.
It has endured and is commonly used without any major problems. In the same figure, a cooling air seal plate blade side insertion groove 5 into which a cooling air seal plate end (to be described later) is inserted is cut on the lower side of the downstream end of the blade platform in the direction of the blade wheel.
一方、軸方向翼止装置には、図示しないが、その動翼々
根部の形状、翼車の構造、冷却方式等に応じて多種多様
な方式が採用されており、そのいずれも構造が複雑であ
る上に、信頼性に欠ける点があるとされている。On the other hand, although not shown in the figures, various types of axial blade stop devices are adopted depending on the shape of the rotor blade root, the structure of the impeller, the cooling method, etc., and all of them have complex structures. The above points are said to be unreliable.
発明が解決しようとする問題点
この発明は、特に高温に暴露されるタービン動翼の軸方
向翼止装置を構造簡単、かつ信頼性充分に構成させるこ
とにある。Problems to be Solved by the Invention The object of the present invention is to provide a simple structure and a highly reliable axial blade stop device for turbine rotor blades which are particularly exposed to high temperatures.
問題点を解決するための手段
この発明は、各動翼の後流側にその上、下部端を翼プラ
ットフォーム部および翼車の夫々の挿入溝に嵌入させて
架設してある冷却空気シール板の上流側の下部に回り止
めを突設して翼車溝部内に挿入させるとともに、前記シ
ール板の下部端および翼車側挿入溝底間に最終架設シー
ル板を除いて夫々真正めキーを円周方向から嵌入させ、
さらに該最終架設シール板の回り止めの下方の翼車の両
側に削設させた板ばね挿入溝に跨状板ばねの両足端を挿
嵌させて載板ばねで前記回り止めを下方から弾圧させて
なるものである。Means for Solving the Problems This invention provides a cooling air seal plate installed on the downstream side of each rotor blade with its lower end fitted into the respective insertion grooves of the blade platform portion and the blade wheel. A detent is protruded from the lower part of the upstream side to be inserted into the blade wheel groove, and a key is inserted circumferentially between the lower end of the seal plate and the bottom of the blade wheel side insertion groove, excluding the final seal plate. Insert it from the direction,
Furthermore, both leg ends of the straddle leaf spring are inserted into leaf spring insertion grooves cut on both sides of the impeller below the rotation stopper of the final installed seal plate, and the plate springs are used to press the rotation stopper from below. This is what happens.
作用
したがって、この発明の構成によれば、最終架設シール
板を除いた各動翼および翼車間に架設させである冷却空
気シール板の下部端および翼車側挿入溝底間に嵌入させ
た真正めキーが該シール板を上方に緊締しているととも
に、最終架設シール板をその両足端を翼車の板ばね挿入
溝内に抑承させた跨状板ばねが該最終シール板の回り止
めを上方に押圧しているから、前記シール板のすべてが
常に翼プラットフォーム部および翼車間の正規な嵌合状
態に保持させられることになり、翼の軸方向の抜は止め
に該シール板が役立つとともに、前記シール板の円周方
向の移動を前記回り止めが翼車溝部内に挿入して防止す
る。Operation Therefore, according to the configuration of the present invention, the cooling air seal plate, which is installed between each rotor blade and the blade wheel except for the final installed seal plate, is fitted between the lower end of the cooling air seal plate and the bottom of the insertion groove on the blade wheel side. The key tightens the seal plate upward, and the straddle leaf spring, which holds both leg ends of the final installed seal plate in the leaf spring insertion groove of the impeller, prevents the final seal plate from rotating upward. Since all of the seal plates are pressed against each other, all of the seal plates are always maintained in a properly fitted state between the blade platform portion and the blade wheel, and the seal plates serve to prevent the blade from being pulled out in the axial direction. The rotation stopper is inserted into the impeller groove to prevent movement of the seal plate in the circumferential direction.
実施例
つぎに、この発明の実施例を示す図面によって説明する
と、第１，２，３および４図において、ガス流れ１４中
に暴露している翼フロフィル部１を突設した翼プラット
フォーム部２の翼りヤンク部３先端部のクリスマスツリ
一部４は翼車６にその軸方向に圧入させられるとともに
、前記翼プラットフォーム部の後流側端の下側に冷却空
気シール板翼側挿入溝５を円周方向に、また該真個挿入
溝の下方の翼車６にも冷却空気シール板翼車側挿入溝８
を同様に夫々別設させ、前記両挿入溝間にはその下部に
回り止め１１を突設している下流側冷却空気シール板７
をその上、下部端を夫々前記挿入溝内に嵌入し、かつ前
記回り止めを上流側に指向して翼車溝部内に挿入させて
架設させ、さら ゛に最終架設シール板を除いた他の前
記シール板の各々の下部端および前記翼車側挿入溝底間
に真正めキー９を円周方向から圧入させて該シール板を
固定し、また前記最終架設シール板の回り止めＬｌの下
方の前記翼車の両側に各々板ばね挿入翼車溝１５を削設
させて該挿入翼車溝に跨状板ばね１２の両足端を挿嵌さ
せて載板ばねの中央部分で前記回り止めを下方から押上
げるようにして最終架設クール板を固定しく第３および
４−）でなるもので、なお、動翼の上流側には上流側冷
却空気シール板１０を架設させ、また動翼のクリスマス
ツリ一部４底面および翼車の前記ツリ一部圧大溝間の空
洞部に冷却空気だまり１３が形成され、さらに前記冷却
空気シール板の各々の両側には第２図に示すように凹凸
部１６を形成してあって該シール板の架設時にその両隣
接シール板の両側が順次嵌合するようにしてある。DESCRIPTION OF THE PREFERRED EMBODIMENTS Referring now to FIGS. 1, 2, 3 and 4, an embodiment of the invention will be described. In FIGS. The Christmas tree part 4 at the tip of the wing yank section 3 is press-fitted into the impeller 6 in its axial direction, and a cooling air seal plate wing-side insertion groove 5 is circularly inserted under the trailing end of the wing platform section. In the circumferential direction, and also in the blade wheel 6 below the true piece insertion groove, there is a cooling air seal plate blade wheel side insertion groove 8.
A downstream cooling air seal plate 7 is provided separately, and a detent 11 is protruded from the lower part between the two insertion grooves.
Further, the lower ends of the blades are inserted into the insertion grooves, and the detents are inserted into the impeller grooves with the detents facing upstream to construct the blade, and further, the other blades except for the final construction seal plate are installed. A straight key 9 is press-fitted from the circumferential direction between the lower end of each of the seal plates and the bottom of the impeller side insertion groove to fix the seal plates, and the lower end of the detent Ll of the final installed seal plate is A leaf spring insertion blade wheel groove 15 is cut on each side of the blade wheel, and both leg ends of the straddle leaf spring 12 are inserted into the insertion blade wheel groove, and the rotation stopper is lowered at the center of the plate spring. The final cooling air seal plate 10 is installed on the upstream side of the rotor blade, and the Christmas tree on the rotor blade is fixed. A cooling air pocket 13 is formed in the bottom surface of part 4 and in the cavity between the tree and the large pressure groove of the impeller, and furthermore, uneven parts 16 are formed on both sides of each of the cooling air seal plates as shown in FIG. The seal plate is formed so that both adjacent seal plates are fitted in sequence when the seal plate is installed.
ついで、この発明に係るタービン動翼の軸方向翼止装置
の組立について説述すると、まず上流側冷却空気シール
板１０を翼車６の外周に挿入してから、該翼車に動翼お
よび下流側冷却空気シール接シール板挿入溝８から挿入
させ（第２および４図）、こ、のようにして順次に動翼
、シール板および真正めキーを翼車円周に植込んだ後に
、最終架設シール板に対しては該真正めキーの挿入がで
きないから、まず跨状板ばね１２を板ばね挿入翼車溝１
５にその両足端を挿嵌させ、つぎに該シール板°をその
回り止め１１によって前記跨状板ばねな押えて載板ばね
を変形させながら、その下部端をシール板翼車側挿入溝
８内に挿入してから、前記シール板の上部端が真個挿入
溝５内に嵌入できる位置で手を離すと、該シール板は前
記跨状板ばねの反力によってその上部端が前記真個挿入
溝内に嵌入して架設を終えることになるが、その際にす
べてのシール板の回り止め１１が翼車溝部内に挿入する
ことになるもので、したがって動翼の軸方向への移動が
阻止されるとともに、各シール板の回り止めが翼車溝部
内に挿入しているのでシール板の円周方向への移動が防
止され、さらに運転中は、翼止めキー９によって固定さ
れた冷却空気シール板７はその半径方向の移動を阻止さ
れて脱落することがなく、跨状板ばね１２で押上げられ
て所定位置を保持している最終架設シール板は載板ばね
に負荷する遠心力がその取付形状を維持する方向に働く
ため゛になお一層確実に所定位置に保持されるとともに
、前記板ばねが最も低い応力がかかる取付時形状にある
から、クリープ、塑性変形を起こすことがなく、シたが
って取付は時の信頼性を損なう事態を招くことがない。Next, the assembly of the axial blade stop device for a turbine rotor blade according to the present invention will be described. First, the upstream cooling air seal plate 10 is inserted into the outer periphery of the blade wheel 6, and then the rotor blade and the downstream side are inserted into the blade wheel. Insert the side cooling air seal through the seal plate insertion groove 8 (Figures 2 and 4), and after sequentially inserting the moving blade, seal plate, and straight key into the circumference of the blade wheel as shown, the final Since the straight key cannot be inserted into the installed seal plate, first insert the straddle leaf spring 12 into the leaf spring insertion blade wheel groove 1.
Next, the lower end of the seal plate is inserted into the seal plate impeller side insertion groove 8 while deforming the plate spring by deforming the plate spring by pressing the seal plate with the detent 11. When the upper end of the seal plate is inserted into the true piece insertion groove 5 and the hand is released, the upper end of the seal plate is pushed into the true piece insertion groove 5 by the reaction force of the straddle leaf spring. The installation will be completed by fitting into the insertion groove, but at this time all the rotation stoppers 11 of all the seal plates will be inserted into the impeller groove, so the movement of the rotor blade in the axial direction will be prevented. In addition, since the detent of each seal plate is inserted into the blade wheel groove, movement of the seal plate in the circumferential direction is prevented. Furthermore, during operation, the cooling air that is fixed by the blade stopper key 9 is prevented from moving in the circumferential direction. The seal plate 7 is prevented from moving in the radial direction and does not fall off, and the final installed seal plate, which is pushed up by the straddle plate spring 12 and held in a predetermined position, is protected against the centrifugal force applied to the plate spring. Since the leaf spring works in the direction of maintaining its installed shape, it is held in place even more reliably, and since the leaf spring is in the installed shape where the lowest stress is applied, creep and plastic deformation do not occur. Therefore, the installation will not result in a situation where reliability is impaired.
発明の効果
上述したように、この発明は、タービン動翼の軸方向翼
止装置として従来技術にない確実な信頼性を発揮できる
上に、負荷される遠心力、熱応力、熱衝撃力等に充分耐
えられることができ、しかも構造的には極めて簡単であ
るなど、産業上の利用価値の大きい発明である。Effects of the Invention As described above, the present invention is capable of exhibiting reliable reliability that is not available in the prior art as an axial blade stop device for turbine rotor blades, and is also able to withstand applied centrifugal force, thermal stress, thermal shock force, etc. It is an invention with great industrial utility value, as it is sufficiently durable and has an extremely simple structure.
第１図は、この発明の実施例を示す要部を切断面であら
れした翼止めキーを挿入させた冷却空気シール板部位の
縦断側面図、第２図は、前図のシール板要部をＡ−Ａ方
向からの斜視であられした矢視図、第３図は、この発明
の実施例を示す要部を切断面であられした跨状板ばねで
押圧した最終架設シール板部位の縦断側面図、第４図は
、前図のシール板要部なり−Ｂ方向からの矢視図、第５
図は、空気冷却式ガスタービン動翼例を示す斜視図であ
る。
１・・翼プロフィル部、２・・翼プラットフォーム部、
３・・翼シャンク部、４・・クリスマスツリ一部、５・
・冷却空気シール板翼側挿入溝、６・・翼車、７・・下
流側冷却空気シール板、８・・冷却空気シール板翼車側
溝、９・・翼止めキー、１０・・上流側冷却空気シール
板、１１・・回り止め、１２・・跨状板ばね、１３・・
冷却空気だまり、１４・・ガス流れ、１５・・板ばね挿
入翼車溝、１６・・シール板両側凹凸部。
（ほか７名）
第１図
第２図
第３図
第４図
第５図Fig. 1 is a longitudinal cross-sectional side view of a cooling air seal plate portion showing an embodiment of the present invention, in which a blade stopper key whose main part is cut with a cut surface is inserted, and Fig. 2 shows a main part of the seal plate shown in the previous figure. FIG. 3 is a cross-sectional side view of the final erected seal plate portion, showing an embodiment of the present invention, in which the main part is pressed by a straddle plate spring with a cut surface. , Figure 4 is the main part of the seal plate in the previous figure, a view taken from arrow B, and Figure 5.
The figure is a perspective view showing an example of an air-cooled gas turbine rotor blade. 1. Wing profile section, 2. Wing platform section,
3. Wing shank part, 4. Part of Christmas tree, 5.
・Cooling air seal plate blade side insertion groove, 6...Blade wheel, 7...Downstream side cooling air seal plate, 8...Cooling air seal plate blade wheel side groove, 9...Blade stop key, 10...Upstream side cooling air Seal plate, 11... Rotation stopper, 12... Straddle leaf spring, 13...
Cooling air pool, 14. Gas flow, 15. Leaf spring insertion impeller groove, 16. Irregularities on both sides of seal plate. (7 others) Figure 1 Figure 2 Figure 3 Figure 4 Figure 5
Claims (1)
部および翼車の夫々の挿入溝に嵌入させて架設してある
冷却空気シール板の上流側の下部に回り止めを突設して
翼車溝部内に挿入させるとともに、前記シール板の下部
端および翼車側挿入溝底間に最終架設シール板を除いて
夫々翼止めキーを円周方向から嵌入させ、さらに該最終
架設シール板の回り止めの下方の翼車の両側に削設させ
た板ばね挿入溝に跨状板ばねの両足端を挿嵌させて該板
ばねで前記回り止めを下方から弾圧させることを特徴と
するタービン動翼の軸方向翼止装置。A detent is provided protruding from the lower part of the upstream side of the cooling air seal plate, which is installed on the downstream side of each rotor blade and whose lower end is fitted into the respective insertion grooves of the blade platform part and the blade wheel. At the same time, a blade stopper key is inserted between the lower end of the seal plate and the bottom of the impeller side insertion groove from the circumferential direction, excluding the final installed seal plate, and A turbine engine characterized in that both leg ends of a straddle leaf spring are inserted into leaf spring insertion grooves cut on both sides of the impeller below the detent, and the leaf springs press the detent from below. Axial wing stop device for the wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4269085A JPS61205303A (en) | 1985-03-06 | 1985-03-06 | Stopper in axial direction for turbine moving blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4269085A JPS61205303A (en) | 1985-03-06 | 1985-03-06 | Stopper in axial direction for turbine moving blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS61205303A true JPS61205303A (en) | 1986-09-11 |
Family
ID=12643032
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4269085A Pending JPS61205303A (en) | 1985-03-06 | 1985-03-06 | Stopper in axial direction for turbine moving blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS61205303A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01144401U (en) * | 1988-03-29 | 1989-10-04 | ||
| JP2010180879A (en) * | 2009-02-05 | 2010-08-19 | General Electric Co <Ge> | Turbine coverplate system |
| JP2010216657A (en) * | 2009-03-12 | 2010-09-30 | General Electric Co <Ge> | Machine seal assembly |
| JP2021535975A (en) * | 2018-07-23 | 2021-12-23 | シーメンス エナジー グローバル ゲゼルシャフト ミット ベシュレンクテル ハフツング ウント コンパニー コマンディートゲゼルシャフトSiemens Energy Global Gmbh & Co. Kg | Flow guide for cooling turbine blades and turbine blade cooling method |
-
1985
- 1985-03-06 JP JP4269085A patent/JPS61205303A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01144401U (en) * | 1988-03-29 | 1989-10-04 | ||
| JP2010180879A (en) * | 2009-02-05 | 2010-08-19 | General Electric Co <Ge> | Turbine coverplate system |
| JP2010216657A (en) * | 2009-03-12 | 2010-09-30 | General Electric Co <Ge> | Machine seal assembly |
| EP2236768A3 (en) * | 2009-03-12 | 2014-12-24 | General Electric Company | Turbomachine seal assembly |
| JP2021535975A (en) * | 2018-07-23 | 2021-12-23 | シーメンス エナジー グローバル ゲゼルシャフト ミット ベシュレンクテル ハフツング ウント コンパニー コマンディートゲゼルシャフトSiemens Energy Global Gmbh & Co. Kg | Flow guide for cooling turbine blades and turbine blade cooling method |
| US11377956B2 (en) | 2018-07-23 | 2022-07-05 | Siemens Energy Global GmbH & Co. KG | Cover plate with flow inducer and method for cooling turbine blades |
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