JPS60173302A - Moving blade implanting equipment for gas turbine - Google Patents

Moving blade implanting equipment for gas turbine

Info

Publication number
JPS60173302A
JPS60173302A JP59028553A JP2855384A JPS60173302A JP S60173302 A JPS60173302 A JP S60173302A JP 59028553 A JP59028553 A JP 59028553A JP 2855384 A JP2855384 A JP 2855384A JP S60173302 A JPS60173302 A JP S60173302A
Authority
JP
Japan
Prior art keywords
turbine
packet
wheel
tip
gas turbine
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
Application number
JP59028553A
Other languages
Japanese (ja)
Inventor
Hisataka Momozaki
百崎　尚隆
Fumiyuki Hirose
文之 広瀬
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hitachi Service Engineering Co Ltd
Hitachi Ltd
Original Assignee
Hitachi Service Engineering Co Ltd
Hitachi Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Hitachi Service Engineering Co Ltd, Hitachi Ltd filed Critical Hitachi Service Engineering Co Ltd
Priority to JP59028553A priority Critical patent/JPS60173302A/en
Publication of JPS60173302A publication Critical patent/JPS60173302A/en
Pending legal-status Critical Current

Links

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE:To enable turbine buckets to be pulled out or implanted one by one by fabricating dovetail grooves for both a turbine bucket and a turbine wheel 12 in such a manner that the grooves form a circular arc whose center coincides with the center of a tip shroud. CONSTITUTION:Dovetail grooves 10 for both a turbine bucket 8 and a turbine wheel 12 are machined in a circular arc so that they form a part of a circle with radius 24 and whose center is the intersection 23 between the middle line 22 of the plate thickness in the radial direction 15 of a tip shroud 16 located at the tip of a bucket 8 and the middle line 21 in the axial direction 11 of the tip shroud 16. With this contrivance, the buckets 8 can be pulled out from or implanted to the wheel 12 one by one without causing interference among the tip shrouds 16.

Description

【発明の詳細な説明】 〔発明の利用分野〕 本発明は、ガスタービン用バゲツ１−の植込み溝の加工
形状に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Application of the Invention] The present invention relates to the processing shape of a planting groove of a baguette 1- for a gas turbine.

〔ｇ５明の背景〕 第１図はガスタービンの断面図である。空気１は圧縮機
部２で圧縮され、燃焼器３に流入し、そこで、燃料と混
合され、燃焼し、高湿となった燃焼ガス４は、第１段タ
ービン入ロノズル５を通り、第１段パケット６に当り、
タービンロータ９を回転させる。さらに、燃焼ガス４は
、第２段タービン入口ノズル７を経て、第２段バケツｌ
−８ｋ：：作用する。[Background of G5 Light] FIG. 1 is a cross-sectional view of a gas turbine. The air 1 is compressed by the compressor part 2 and flows into the combustor 3, where it is mixed with fuel and combusted, and the highly humid combustion gas 4 passes through the first stage turbine input nozzle 5 and is transferred to the first stage turbine. For stage packet 6,
Rotate the turbine rotor 9. Furthermore, the combustion gas 4 passes through the second stage turbine inlet nozzle 7, and the second stage bucket l.
-8k::acts.

第２図に、第２段パケットの構造を示す。パケットは、
ダブテール１．　Ｏと呼ばれる軸方向１１に直線に切ら
れた溝により、タービンホイールｊ２に植え込まれてい
る。ダブテールの底には、ツイストロックピン１３と呼
ばれる軸方向１１の外れ防止用ピンをもっている。FIG. 2 shows the structure of the second stage packet. The packet is
Dovetail 1. A groove cut straight in the axial direction 11, called O, is implanted in the turbine wheel j2. The bottom of the dovetail has a pin called a twist lock pin 13 to prevent it from coming off in the axial direction 11.

通常、ガスタービンでは、第２段目以降のバケツ１−は
、第１段パケットに較べ、翼部１４が長いため、運転中
は、高温燃焼ガス通過に伴い、半径方向１５の熱伸びが
非常に大きくなってしまう。Normally, in a gas turbine, the buckets 1- in the second and subsequent stages have longer blade portions 14 than the first-stage packets, so during operation, thermal expansion in the radial direction 15 is extremely large due to the passage of high-temperature combustion gas. It gets bigger.

そこで、もはや、第１段パケット６のように、パケット
先端の間隙を小さくし、燃焼ガスのパケット先端まわり
からの漏れを少なくすることは、不可能となり、第２段
以降のパケットでは、チップシュラウド１６と呼ばれる
燃焼ガス漏れ防止用の一種のシールをもつ構造となって
いる。Therefore, it is no longer possible to reduce the gap between the tips of the packets and reduce the leakage of combustion gas from around the tips of the packets, as in the case of the first stage packet 6. It has a structure with a type of seal called 16 to prevent combustion gas leakage.

第３図は、そのチップシュラウド１６を半径方面外側か
ら見たものである。隣り合うチップシュラウド間は、運
転中の高温燃焼ガス通過に伴う、チップシュラウドの周
方向１７の熱伸びによる、隣り合うチップシュラウドど
おしの接触をさけるために、周方向間隙１８を設けてい
る。ところが近年、ガスタービンの高効率化が図られ、
燃焼ガスの漏れを極力少なくする目的で、チップシュラ
ウド１６間の継なぎ目を本図に示すように、ジグザグに
して組み合わせ、燃焼ガスのチンブシュラウド部におけ
る軸方向１９の漏れをさまたげるラビリンス効果をねら
っている。FIG. 3 shows the tip shroud 16 viewed from the outside in the radial direction. A circumferential gap 18 is provided between adjacent tip shrouds in order to avoid contact between adjacent tip shrouds due to thermal expansion in the circumferential direction 17 of the tip shroud due to the passage of high-temperature combustion gas during operation. . However, in recent years, efforts have been made to improve the efficiency of gas turbines,
In order to minimize the leakage of combustion gas, the joints between the tip shrouds 16 are combined in a zigzag pattern as shown in this figure to create a labyrinth effect that prevents combustion gas from leaking in the axial direction 19 at the tip shroud. Aiming.

ガスタービンのバケツ１へは、運転中に、異物が混入、
衝突し、全バケツ１−のうり１本あるいは、何本かが、
破損したり、クラックを生じることがある。その場合、
そのパケットだけをホイールからぬき取り補修あるいは
、交換をしたいわけであるが、前述のように、パケット
の先端についたチップシュラウド部１Ｇは、となりのチ
ップシュラウド部と組み合わさっているため第４図に示
すように１本の破損パケット２０だけをぬき取りたい場
合でも、まわりの健全なパケットまでもホイール１２か
らぬき取る必要があり、多大な交換作業時間を要し、抜
き取ったパケットの番号管理が必要となり、ガスタービ
ンの保守、点検作業時に、非常な障害となり、また、健
全なパケットをひんばんにたたいてホイールから抜き取
ったり、植え込んだりすることから、パケットやホイー
ルのダブテール部をいためたりすることから製品の品質
維持の面からも好ましくなかった。During operation, foreign matter may enter bucket 1 of the gas turbine.
A collision occurs, and one or more gourds in the whole bucket 1-
It may break or crack. In that case,
I would like to remove just that packet from the wheel and repair or replace it, but as mentioned above, the chip shroud part 1G attached to the tip of the packet is combined with the adjacent chip shroud part, so it is shown in Figure 4. Even if it is desired to remove only one damaged packet 20 as shown, it is necessary to remove the surrounding healthy packets from the wheel 12 as well, which requires a lot of time for replacement work and requires number management of the extracted packets. This can become a serious hindrance during gas turbine maintenance and inspection work, and the dovetails of the packets and wheels can be damaged as healthy packets are frequently struck and removed from the wheel, or implanted. This was also unfavorable from the standpoint of maintaining product quality.

〔発明の目的〕[Purpose of the invention]

本発明の目的は、パケットを一本毎にタービンホイール
から抜き取ったり、植え込んだりすることを可能とする
タービン動翼を提供するにある。SUMMARY OF THE INVENTION An object of the present invention is to provide a turbine rotor blade that allows packets to be removed from and inserted into a turbine wheel one by one.

〔発明の概要〕[Summary of the invention]

本発明はタービンパケットとタービンホイールのダブテ
ール溝を、パケットのチップシュラウド部の中央を中心
とする円弧で形状加工することにより、チップシュラウ
ドが相互に干渉することなく、バケツ１〜の抜き取り、
植え込みができるようにしたことを特徴とする。In the present invention, the dovetail grooves of the turbine packet and the turbine wheel are shaped into circular arcs centered on the center of the chip shroud part of the packet.
It is characterized by being able to be planted.

〔発明の実施例〕[Embodiments of the invention]

第５図は、タービンホイールの断面図であり、軸方向１
１に沿ってホイール１２を断面し、パケット８との関係
を表わしたものである。以下、本発明の特徴となってい
るタービンホイールとパケットのダブテール１０の溝加
工法について説明する。パケット８の先端についたチッ
プシュラウド１６の半径方向１５板厚中央線２２と、軸
方向１１のチップシュラウド中央線２１との交点２３を
中心とする半径２４の円の円弧で、タービンホイール１
２とパケット８のダブテール１０の溝を加工する。FIG. 5 is a cross-sectional view of the turbine wheel, with the axial direction 1
The wheel 12 is sectioned along the line 1 and its relationship with the packet 8 is shown. Hereinafter, a method of grooving the dovetail 10 of a turbine wheel and packet, which is a feature of the present invention, will be explained. The turbine wheel 1 is an arc of a circle with a radius 24 centered on the intersection 23 of the thickness center line 22 of the chip shroud 16 in the radial direction 15 attached to the tip of the packet 8 and the chip shroud center line 21 in the axial direction 11.
2 and the grooves of the dovetail 10 of the packet 8 are machined.

第６図に本発明のタービンパケット８の抜き取り要領を
示す。運転中にパケットが移動するのを防ぐツイストロ
ックピン１３を半回転し、ロックを解除し、チップシュ
ラウドＩ６上の交点２３の回り２５にパケット８を回す
ことにより、チップシュラウド１６は、軸方向１１に移
動することなく、つまり、隣り合うバケツ１−のチップ
シュラウドと干渉することなく、タービンホイール１２
がら抜き取ることが可能となる。FIG. 6 shows a procedure for extracting the turbine packet 8 of the present invention. By turning the twist locking pin 13, which prevents the packet from moving during operation, by half a turn, unlocking it, and turning the packet 8 around the intersection point 23 on the chip shroud I6 25, the chip shroud 16 is secured in the axial direction 11. The turbine wheel 12
It becomes possible to pull it out.

第７図は、破損したバケツ１〜２０を１本のみタービン
ホイール１２から抜き取るのを示す斜視図である。この
図からも、チップシュラウド１６は、隣り合うチップシ
ュラウドに干渉せずに、バケツ１−２０を抜き取れるこ
とがわかる。また、バケツ１〜をホイールに植え込む場
合は、以上に述べてきた逆の手順で可能となる。FIG. 7 is a perspective view showing how only one of the damaged buckets 1 to 20 is removed from the turbine wheel 12. This figure also shows that the tip shroud 16 allows the bucket 1-20 to be extracted without interfering with adjacent tip shrouds. Furthermore, when buckets 1 to 1 are to be placed in the wheel, this can be done by reversing the procedure described above.

次に１本発明の実現に際し、好ましいライストロラクビ
ンについて説明する。Next, lystrolacvin, which is preferable for realizing the present invention, will be explained.

第８図は、従来までのライストロツクピン１３を使用し
、ホイール１２にパケットダブテール１０を固定したも
のである。ツイストロックピンは、円柱の両端に、バケ
ツ１−ダブテール１ｏをひっかける半月状の皿をもち、
パケットをロックする時は、円柱部からオーバーハング
したこの皿部が上にくるようにし、また、パケットを取
りはずす場合には、半回転して、このオーバーハングし
た皿部が下にきてパケットの取り除きを可能としたピン
である。FIG. 8 shows a packet dovetail 10 fixed to a wheel 12 using a conventional right lock pin 13. The twist lock pin has half-moon-shaped plates on both ends of the cylinder that hook the bucket 1 - dovetail 1o.
When locking the packet, make sure that the plate that overhangs from the cylindrical part is at the top, and when removing the packet, turn it half a turn so that the overhanging plate comes to the bottom of the packet. This is the pin that made it possible to remove it.

本図で示すように、パケットダブテール１０を円弧状に
加工したことにより、バケットダブテール１０の両端は
、上方にせり上がっており、ライスト［１ツクピン１３
とのひっかかり高さ２Ｇは小さくなっている。このひっ
かかり高さ２６を大きくするには、このツイスト・ロッ
クピン１３の皿部のオーバーハングを大きくすればよい
が、そうした場合この皿部の強度が低下することが考え
られる。そこで、第９図に示すように、このツイストロ
ックピン１３のピン部の形状がダブテールｌＯの円孤形
状に沿うよ−）に、ピンの両端に近づくにつれてピン径
が太くなるようにする。これに伴い、タービンホイール
１２のダブ子−ル溝導部も、ライストロツクピン１３が
スムーズに回転できるように、両端の孔径が除々に大き
くなるように加工する。これにより、ツイストロックピ
ンｉａｊ　＠の皿部は、オーバーハングが従来と同じで
あってもひっかかり高さ２６も同じにすることができる
。As shown in this figure, by processing the packet dovetail 10 into an arc shape, both ends of the bucket dovetail 10 rise upward, and the right [1 pin 13]
The catching height 2G between the two has become smaller. In order to increase the hooking height 26, the overhang of the plate portion of the twist lock pin 13 may be increased, but in this case, the strength of the plate portion may be reduced. Therefore, as shown in FIG. 9, the shape of the pin portion of this twist lock pin 13 is made so that it follows the arc shape of the dovetail lO, and the pin diameter increases as it approaches both ends of the pin. Along with this, the double ring groove guide portion of the turbine wheel 12 is also machined so that the diameter of the hole at both ends becomes gradually larger so that the right lock pin 13 can rotate smoothly. Thereby, the plate portion of the twist lock pin iaj@ can have the same hooking height 26 even if the overhang is the same as the conventional one.

〔発明の効果〕〔Effect of the invention〕

本発明によれば、ガスタービンパケットの抜き取り、植
え込みが容易になり、作業工数が低減でき、メインテナ
ンス」ス１への大幅低減が可能である。According to the present invention, it becomes easy to extract and install the gas turbine packet, and the number of man-hours can be reduced, making it possible to significantly reduce the amount of maintenance required.

【図面の簡単な説明】[Brief explanation of the drawing]

第１図はガスタービンの断面図、第２図は従来のパケッ
トとタービンホイールの斜視図、第３図はパケットのチ
ップシュラウドの並びを半径方向外側から見た図、第４
図はパケットに破損が生じた場合の交換を示す斜視図、
第５図は本発明のタービンホイールとパケットのダブテ
ールの関係を示すホイールの断面図、第６図は本発明の
タービンパケットの抜き取り要領図、第７図は、本発明
のダブテール溝をもつ破損パケットを１本のみタービン
ホイールから抜き取るのを示す斜視図、第８図は本発明
のダブテール溝をもつタービンパケットを従来までのラ
イスｊ・ロックピンで固定した場合を示す図、第９図は
本発明のダブテール溝をもつタービンバケツ１−を、本
発明によるライストロツクピンを使って固定した場合を
示す図である。 １０・・・ダブテール、１２・・・ホイール、１３・・
・ツイストロックピン、２６・・・ひっががり高さ。 代理人　弁理士　高橋明夫 第１ｍ 第２閃Figure 1 is a cross-sectional view of a gas turbine, Figure 2 is a perspective view of a conventional packet and turbine wheel, Figure 3 is a view of the array of chip shrouds in the packet viewed from the outside in the radial direction, and Figure 4 is a perspective view of a conventional packet and turbine wheel.
The figure is a perspective view showing replacement if the packet is damaged.
Fig. 5 is a sectional view of the wheel showing the relationship between the turbine wheel of the present invention and the dovetail of the packet, Fig. 6 is a diagram showing how to remove the turbine packet of the present invention, and Fig. 7 is a damaged packet with dovetail grooves of the present invention. FIG. 8 is a perspective view showing a turbine packet having a dovetail groove of the present invention being fixed with a conventional rice j/lock pin, and FIG. 9 is a perspective view showing a turbine packet of the present invention being removed from a turbine wheel. 1 is a diagram showing a case where a turbine bucket 1- having a dovetail groove is fixed using a right lock pin according to the present invention. 10... Dovetail, 12... Wheel, 13...
・Twist lock pin, 26...Holding height. Agent Patent Attorney Akio Takahashi 1st m 2nd flash

Claims (1)

【特許請求の範囲】 １、ガスタービンバスケットの植込み溝が、円孤状とな
っていることを特徴とするガスタービン動翼。 ２、特許請求の範囲第１項において、さらに前記植込み
溝底のツイストロックピンの形状を両端に近づくにつれ
て大径としたことを特徴とする植込み装置。[Scope of Claims] 1. A gas turbine rotor blade characterized in that the implantation groove of the gas turbine basket is arc-shaped. 2. The implantation device according to claim 1, further characterized in that the shape of the twist lock pin at the bottom of the implantation groove becomes larger in diameter as it approaches both ends.
JP59028553A 1984-02-20 1984-02-20 Moving blade implanting equipment for gas turbine Pending JPS60173302A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP59028553A JPS60173302A (en) 1984-02-20 1984-02-20 Moving blade implanting equipment for gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP59028553A JPS60173302A (en) 1984-02-20 1984-02-20 Moving blade implanting equipment for gas turbine

Publications (1)

Publication Number Publication Date
JPS60173302A true JPS60173302A (en) 1985-09-06

Family

ID=12251843

Family Applications (1)

Application Number Title Priority Date Filing Date
JP59028553A Pending JPS60173302A (en) 1984-02-20 1984-02-20 Moving blade implanting equipment for gas turbine

Country Status (1)

Country Link
JP (1) JPS60173302A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0821133A1 (en) * 1996-07-27 1998-01-28 ROLLS-ROYCE plc Gas turbine engine fan blade retention
US20120014802A1 (en) * 2010-07-14 2012-01-19 General Electric Company Dovetail connection for turbine rotating blade and rotor wheel
US20120034086A1 (en) * 2010-08-04 2012-02-09 General Electric Company Swing axial entry dovetail for steam turbine buckets
JP2012087799A (en) * 2010-10-21 2012-05-10 General Electric Co <Ge> Swing axial-entry for closure bucket used for tangential row in steam turbine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0821133A1 (en) * 1996-07-27 1998-01-28 ROLLS-ROYCE plc Gas turbine engine fan blade retention
US20120014802A1 (en) * 2010-07-14 2012-01-19 General Electric Company Dovetail connection for turbine rotating blade and rotor wheel
US8651820B2 (en) * 2010-07-14 2014-02-18 General Electric Company Dovetail connection for turbine rotating blade and rotor wheel
EP2407637A3 (en) * 2010-07-14 2014-08-27 General Electric Company Dovetail connection for turbine rotating blade and rotor wheel
US20120034086A1 (en) * 2010-08-04 2012-02-09 General Electric Company Swing axial entry dovetail for steam turbine buckets
JP2012087799A (en) * 2010-10-21 2012-05-10 General Electric Co <Ge> Swing axial-entry for closure bucket used for tangential row in steam turbine

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