JPS5832905A - Blade cooling system - Google Patents
Blade cooling systemInfo
- Publication number
- JPS5832905A JPS5832905A JP13014481A JP13014481A JPS5832905A JP S5832905 A JPS5832905 A JP S5832905A JP 13014481 A JP13014481 A JP 13014481A JP 13014481 A JP13014481 A JP 13014481A JP S5832905 A JPS5832905 A JP S5832905A
- Authority
- JP
- Japan
- Prior art keywords
- seal plate
- rotor
- blade
- moving blade
- disk
- 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
- 238000001816 cooling Methods 0.000 title claims abstract description 25
- 239000007943 implant Substances 0.000 claims description 16
- 230000008878 coupling Effects 0.000 abstract 1
- 238000010168 coupling process Methods 0.000 abstract 1
- 238000005859 coupling reaction Methods 0.000 abstract 1
- 230000002093 peripheral effect Effects 0.000 description 4
- 238000007789 sealing Methods 0.000 description 4
- 238000002513 implantation Methods 0.000 description 3
- 241000238413 Octopus Species 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000003292 glue Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 235000012149 noodles Nutrition 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
本発明はタービ／の翼冷却装置ＫＩＤ、特Ｋｎスタービ
ンのり一！に連結された動翼の植込部における冷却空気
の外部への漏洩を防止したＩ−ビンの翼冷却装置に関す
る０
一般にガスタービンにおける動翼拡、高瓢ｆＩス中で使
用され１強い遠心力を受けるため、耐久性を確保す゛る
のに細心の注意が必要である０４１Ｋ。DETAILED DESCRIPTION OF THE INVENTION The present invention is a turbine/blade cooling device KID, special Kn turbine glue! Concerning an I-bin blade cooling system that prevents cooling air from leaking to the outside at the implanted part of the rotor blade connected to the rotor blade, which is generally used in a gas turbine where the rotor blades are expanded and used in a high-speed fI system. 041K, which requires extreme care to ensure durability.
ロータべ連結される動翼の植込部、に高い応力が発生し
、四−夕の材、質が一般に耐熱性に劣るため。This is because high stress occurs in the embedded part of the rotor blades that are connected to the rotor, and the material and quality of the rotor blades generally have poor heat resistance.
十分に動翼を冷却することが必要とされていた・このた
め、動翼の植込部に冷却空気を流して冷却していた＠
本発明は、動翼の植込部における冷却空気の外部への漏
洩を防止して冷却空気が所定の通路を流れるようＫした
シール効果の高いタービンの翼冷却装置を提供すること
を目的とする。It was necessary to sufficiently cool the rotor blades. For this reason, cooling air was flowed through the implanted portion of the rotor blade. It is an object of the present invention to provide a turbine blade cooling device with a high sealing effect that allows cooling air to flow through a predetermined passage while preventing leakage.
以下１図面を参照して本発明の実施例について説明する
〇
第１図において、符号ｌはガスタービンの動翼であ）、
コは動翼Ｉが取り付けられるｖｘ −１であるＯ
動！、の下部には、第１図に示す■雇のシ９ｙり部Ｊを
介して植込部参が設けられている。An embodiment of the present invention will be described below with reference to one drawing.〇In FIG. 1, the symbol l is a rotor blade of a gas turbine),
ko is vx −1 to which the rotor blade I is attached O motion! , an implantable part is provided at the lower part of the part via the bottom part J shown in FIG.
一方、ロータコの外周には、植込部取付溝Ｓを有する褒
状ディスク６が一体に取付けられている０また、動ｌｌ
Ｉ／の稲込部参がロータコの植込部取付１１４ｓＶＣゆ
るやかに係合されることＫより動翼ｌがロータコに連結
されている。そして、互いに連結された動Ｒｔの植込部
亭外側と口°−タコの植込部取付溝の内周面との間には
第３図に示す如く、間ＦＪ７が設けられている。On the other hand, on the outer periphery of the rotor tacho, a reward disk 6 having an implanted part mounting groove S is integrally attached.
The rotor blade l is connected to the rotor tacho by the fact that the Inagome part of I/ is loosely engaged with the rotor tacho's implanted part attachment 114sVC. As shown in FIG. 3, a gap FJ7 is provided between the outside of the implanted part of the movable shaft Rt and the inner circumferential surface of the implanted part mounting groove of the octopus, which are connected to each other.
また、動翼Ｉのシャンク部３の水平方向に突出した下端
１１１部下面と、ロータコの水平方向に突出した外周側
部上面にはそれぞれ周方向に切られたシール板取付溝１
．１が相対向して設けられている０そのシール板取付溝
１． ＩＩ／Ｃはシール板ヂが嵌め込まれ、これｋよ〕
動翼Ｉの植込ｍ参の側部が閉鎖されている。Further, seal plate mounting grooves 1 are cut in the circumferential direction on the lower surface of the horizontally protruding lower end 111 of the shank portion 3 of the rotor blade I, and on the upper surface of the horizontally protruding outer peripheral side of the rotor.
．． The seal plate mounting grooves 1 and 1 are provided facing each other. II/C has a seal plate fitted, which is good.]
The side of the implanted rotor blade I is closed.
また、シーＡ＃榎デの両側には互いに喰い違う位置に連
結用突出片ｆｍが突出して設けられている。Furthermore, connecting protruding pieces fm are provided on both sides of the sea A# at mutually different positions.
シアル板デに相対する動翼ｌの植込部参の側部面には第
参図に示すように局方向に円形溝１０が設けられている
。As shown in the figure, a circular groove 10 is provided in the side surface of the implanted portion of the rotor blade l facing the shear plate D in the direction of the blade.
また、シール榎デに相対する四−夕２の褒状ディスク遥
の側部面には第！゛図に示すように上部を残して略全体
に円形溝１０と連通す仝凹所／／が設は飢れ、その凹所
／ｌの上部内周面／／ａと下部内周面／麺線弧状に形、
成されている。In addition, there is a number on the side of the Shi-Yu 2 award disk Haruka that faces the seal Enoki!゛As shown in the figure, there is a recess // that communicates with the circular groove 10 almost entirely except for the upper part, and the upper inner peripheral surface //a of the recess /l and the lower inner peripheral surface /noodle Shaped like an arc,
has been completed.
上記植込部参の円形ｆｌｌｔｏと凹所ｔｉにはシーー用
ワイヤ／Ｊが装入されてｉる・
更に、四−タコのシール板取付震ＩＩ／ＣＦｉ第９図に
示す如く、シール榎ツが一枚斜めに人や込むことのでき
る深溝１３が設けられてぃ−る。The seal wire/J is inserted into the circular flIto and recess ti of the above-mentioned implantation part.Furthermore, as shown in Fig. A deep groove 13 is provided diagonally into which a person can enter.
この深溝／Ｊｉｉ動真Ｉ動翼−！１のシール板堆付溝ｔ
、Ｈｃシール板ｔｔ−嵌め込むために設けられたもので
、シール板ｔを深ｊｌｌ／ＪＫ斜めに入れた後。This deep groove/Jii moving engine I moving blade-! 1 seal plate groove t
, Hc seal plate tt - Provided for fitting, after inserting the seal plate t diagonally to the depth jll/JK.
シール板取付−ｔ、ｔＹ−係合させて第ｔＨｔｌｃ示す
如く、シール板デを周方向に半枚′分同し込んで組み立
てる。シール叡ヂは深溝ｉｓを利用してシール板欺付溝
＃、ｊＫ次々と局方向ＫＩＩＬ込んで組み立てられる。Attaching the seal plate - t, tY - Engage and assemble the seal plate by inserting half of it in the circumferential direction as shown in tHtlc. The seal plate is assembled by using the deep groove IS to insert the seal plate groove #, jK one after another in the local direction KIIL.
このようにシール板取付溝１，１に係合されたシール板
９杜回９止めピン（図示せず）Ｋよ１周方向Ｋ１１転し
ないように固定されている・かかを構成のタービンの翼
冷却装置にあ嘩て唸動翼ｌの植込部参を冷却する冷却空
気陣は第１図に示す如く、ロータコの中心部から矢印に
示すように流れて植込部参を早過する。更に詳細に述べ
ると、第４図に示す如く、ロータコの中心部から流れて
きた植込部参を冷却する冷却空気陣は動翼ｌの植込部参
の底面とロータコの環状ディスク６に設けられた植込部
散村溝Ｓの底面との間の空間ｉｓを通うて植込部亭の側
部に達した後１点線で示すようＫｉｌ状ディスク１の側
部のシールＩ！ｔで閉鎖された凹所／／内を流れて植込
郁参外側と四−タコの植込部取付溝Ｓの内周面の間に設
けられた間隙ツに流入して植込部参を通過する◎
このとき、シール板ｔはシール板取付溝１，１ＫＦ１間
なく係合されておタ、互いに隣接するシール板デ、！同
志は端部の連結用突出片１１９烏が相互に重な夛合って
十分なシール性を有する。The seal plate 9 engaged with the seal plate mounting grooves 1 and 1 is fixed so as not to rotate in the circumferential direction K11 by the locking pin (not shown). As shown in Figure 1, the cooling air that cools the implants of the rotor blade l by the blade cooling system flows from the center of the rotor tacho as shown by the arrow and quickly passes through the implants. . More specifically, as shown in FIG. 4, the cooling air field for cooling the implants flowing from the center of the rotorcopter is provided on the bottom surface of the implanter of the rotor blade l and on the annular disk 6 of the rotorcopter. After reaching the side of the implant through the space is between the bottom surface of the implant and the bottom of the groove S, the seal I on the side of the kill-shaped disc 1 is inserted as shown by the dotted line. The water flows through the recess closed by T and flows into the gap provided between the outside of the implant and the inner circumferential surface of the implant mounting groove S of the octopus, thereby removing the implant. ◎ At this time, the seal plate t is closely engaged with the seal plate mounting grooves 1, 1KF1, and the adjacent seal plates t, ! The connecting protruding pieces 119 at the end portions overlap each other to provide sufficient sealing performance.
また、植込部参の円形溝１０と褒状ディスク≦の凹所／
／Ｆｃ装入されたクール用ワイヤ／Ｊはガスタービンの
運転中、遠心力により褒状ディスク６の外径側に押され
て植込部参の円形溝１０の上方寄り弧状や内周面１０−
及び環状ディスク４の凹所／／における弧状の上部内周
面／／ ａ ｉＣびりた夛付着すると共にこれらの弧状
の内局面１０ａ、／／ａの影ＩｗＫより、Ｖ−ル板ツの
内面にもびうたｐ封書して冷却空気をシールする〇
以上説明したように本発明のタービ／の興冷劫装置はタ
ービンのロー！外周に設けられた植込部取付溝を有する
褒状ディスクと、上記植込Ｉ１敗取付溝ゆるやかに係合
する動翼の植込部と、上記褒状ディスクの側部面に設け
られた凹所と、上記四−夕及び動翼の側部にそれぞれ設
けられた相対向するシール板取付溝と、上記シール板順
付溝に係合して植込部と環状ディスクの側１部を閉鎖す
るシール板とからなるので、ロータの中心部から動翼の
植込部底面とＨディスクの植込部数付溝底面間を通って
植込部の側部に達し、ｌＩ状ディスクの凹所に冷却空気
が流入しても植込部と環状ディスクの側部を閉鎖するシ
ール板が環状ディスクの凹所をシールするため１ｍＩ状
ディスクの凹所内における冷却空気の外部への漏洩が防
止され、有効に冷却空気によって動翼の植込部が冷却さ
れるという効果を奏する。In addition, the circular groove 10 of the implantation part and the recess of the award disk ≦ /
During the operation of the gas turbine, the cool wire /J inserted into the /Fc is pushed toward the outer diameter side of the reward disk 6 by centrifugal force, forming an upward arc of the circular groove 10 in the implantation part and the inner circumferential surface 10-.
And the arcuate upper inner peripheral surface //a iC in the recess //a of the annular disk 4 adheres to the curved inner surface 10a, and from the shadow IwK of these arcuate inner surfaces 10a, //a, on the inner surface of the V-ru plate. Seal the cooling air by sealing the cooling air as described above. An award disk having an implant attachment groove provided on the outer periphery, an implant part of the rotor blade that gently engages with the implant I1 attachment groove, and a recess provided in a side surface of the award disk. , a seal that engages with opposing seal plate mounting grooves provided on the side portions of the rotor blade and the rotor blade, and the seal plate sequential groove to close the implanted portion and a side portion of the annular disk. The cooling air flows from the center of the rotor through the bottom surface of the implanted portion of the rotor blade and the bottom surface of the implanted portion of the H disk to the side of the implanted portion, and into the recess of the II-shaped disk. Even if air flows in, the sealing plate that closes the side of the implant and the annular disc seals the recess of the annular disc, preventing cooling air from leaking to the outside in the recess of the 1 mI disc, effectively cooling the disc. This has the effect that the implanted portion of the rotor blade is cooled by the air.
第１図は本発明のタービンの翼冷却装置を有するロータ
と動翼の組立図、第１図は第１図のＩ［−■線断面図、
第３図は第１図の■−■線断面図。
第参図は同タービンの翼冷却装置における動翼の植込部
を示す部分拡大断面図、第Ｓ図は同タービンの翼冷却装
置におけるロータの褒状ディスクを示す部分拡大断面図
、第６図は同翼冷却装置の分鱗状態を示す一部断面斜視
図゛、第）図は同翼冷却装置のシール板の敢）付は状態
を示す断面図、第を図は同翼冷却装−におけるシール板
の正面図である。
ｌ・・・動翼、コ・・・ロータ、参・・・植込部、ｊ・
・・植込部取付溝、ト・・環状ディスク、ｔ・・−シー
ル板取付溝、デ・・・シール板、ｌｌ・・・凹所。
１１
８２回
第３１
８４目
躬５図FIG. 1 is an assembled view of a rotor and rotor blades having a blade cooling device for a turbine according to the present invention, and FIG. 1 is a sectional view taken along line I[-■ in FIG.
FIG. 3 is a sectional view taken along the line ■-■ in FIG. Figure 6 is a partially enlarged sectional view showing the embedded part of the rotor blade in the blade cooling system of the same turbine, Figure S is a partially enlarged sectional view showing the rotor award disk in the blade cooling system of the same turbine, and Figure 6 is Figures 1 and 2 are partial cross-sectional perspective views showing the state of the blade cooling system in scale. Figures 1 and 2 are cross-sectional views showing the state of the seal plates of the blade cooling system. It is a front view of a board. l... Moving blade, Co... Rotor, Part... Implanted part, j...
... Implant mounting groove, T... annular disk, T... seal plate mounting groove, D... seal plate, ll... recess. 11 82nd No. 31 84th Error Figure 5
Claims (1)
溝を有する褒状ディスクと、上記植込ＩＩ堆付溝にゆる
やかに係合する動翼の植込部と、上１１ｅ１ｍ状−イス
クの側部面に設けられた凹所と、上記−−Ｉ及び動翼の
側部にそれぞれ設けられた相対向するシール板取付溝と
、上記シール板取付溝に係合して植込部と褒状ディスク
の側部を閉鎖するシール板とからなるタービンの翼冷Ｉ
ＩＩＩＩ装置０A reward disk having a groove with an implant IIIE provided on the outer periphery of the rotor of the turbine, an implant part of the rotor blade that gently engages with the groove with the implant II, and a side surface of the upper 11e1m-shaped isk. a recess provided therein, opposing seal plate mounting grooves provided on the sides of the above-mentioned I and rotor blades, and engaging with the seal plate mounting grooves to connect the implanted portion and the side portions of the award disk; A turbine blade cooling I consisting of a seal plate that closes the
III device 0
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP13014481A JPS5832905A (en) | 1981-08-21 | 1981-08-21 | Blade cooling system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP13014481A JPS5832905A (en) | 1981-08-21 | 1981-08-21 | Blade cooling system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS5832905A true JPS5832905A (en) | 1983-02-26 |
Family
ID=15027019
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP13014481A Pending JPS5832905A (en) | 1981-08-21 | 1981-08-21 | Blade cooling system |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5832905A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0270904A (en) * | 1988-07-29 | 1990-03-09 | Westinghouse Electric Corp <We> | turbine rotor assembly |
| JP2007138933A (en) * | 2005-11-16 | 2007-06-07 | General Electric Co <Ge> | Turbine central frame assembly and gas turbine engine for cooling rotor assembly of gas turbine engine |
| JP2017522492A (en) * | 2014-07-17 | 2017-08-10 | シーメンス アクティエンゲゼルシャフト | Wheel disc assembly |
-
1981
- 1981-08-21 JP JP13014481A patent/JPS5832905A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0270904A (en) * | 1988-07-29 | 1990-03-09 | Westinghouse Electric Corp <We> | turbine rotor assembly |
| JP2007138933A (en) * | 2005-11-16 | 2007-06-07 | General Electric Co <Ge> | Turbine central frame assembly and gas turbine engine for cooling rotor assembly of gas turbine engine |
| JP2017522492A (en) * | 2014-07-17 | 2017-08-10 | シーメンス アクティエンゲゼルシャフト | Wheel disc assembly |
| US10378367B2 (en) | 2014-07-17 | 2019-08-13 | Siemens Aktiengesellschaft | Wheel disk assembly |
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