JPS58144605A - Shroud in turbine moving blade - Google Patents

Shroud in turbine moving blade

Info

Publication number
JPS58144605A
JPS58144605A JP2751882A JP2751882A JPS58144605A JP S58144605 A JPS58144605 A JP S58144605A JP 2751882 A JP2751882 A JP 2751882A JP 2751882 A JP2751882 A JP 2751882A JP S58144605 A JPS58144605 A JP S58144605A
Authority
JP
Japan
Prior art keywords
shroud
blade
vane
tenon
tenons
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
JP2751882A
Other languages
Japanese (ja)
Inventor
Yukimasa Okada
岡田　幸正
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries 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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to JP2751882A priority Critical patent/JPS58144605A/en
Publication of JPS58144605A publication Critical patent/JPS58144605A/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
    • F01D5/12—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

Landscapes

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

Abstract

PURPOSE:To reduce the weight of a shroud and thereby providing a vane and a shroud root an increased strength against vibration, by a construction wherein two tenons provided at a top end of moving blade are respectively coupled with tenons of forward and rearward moving blades by strip-shaped shrouds. CONSTITUTION:A turbine moving blade A comprises a vane 3 for receiving a steam flowing from a nozzle blade to produce a rotating energy and a tenon 2 for attaching a shroud adapted to prevent the steam flowing from the nozzle blade from further entering into a gap formed between an outer periphery of the vane 3 and the nozzle blade. In this case, two tenons 2 provided t a top end of the turbine moving blade are respectively coupled with a tenon 2' of a forward vane 3' and a tenon 2'' of a rearward vane 3'' by narrow-profiled shrouds 10a and 10b. This arrangement can remarkably reduce the weight of the shroud, and besides decrease centrifugal forces of the shroud and subsequently of the vane and the blade root area.

Description

【発明の詳細な説明】 本発明は蒸気タービン等の動翼に関するものであり、更
に詳細には、タービン動翼を連結するシュラウドの連結
構造に関するものである。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to rotor blades of steam turbines and the like, and more particularly to a shroud connection structure that connects turbine rotor blades.

従来、例えば蒸気タービンにおいて、第１図及び第２図
に示すように、ケーシングの内部には、回転体であるロ
ータが複数のディスク（図示せず）をともなっている。Conventionally, in a steam turbine, for example, as shown in FIGS. 1 and 2, a rotor, which is a rotating body, is provided with a plurality of disks (not shown) inside a casing.

ディスクの外周部の円周には熱エネルギを回転エネルギ
に変換すべき多数の動翼穴が放射状に植込まれている。A large number of rotor blade holes for converting thermal energy into rotational energy are radially implanted around the outer circumference of the disk.

動翼穴は、ディスクの外周部に植込まれる翼根部（４）
を備え、ノズル翼から流出する蒸気を受け、回転エネル
ギを生じる羽根（３）及びノズル翼から流出した蒸気が
清快の外周部とノズル翼との間隙に流出し、蒸気ターピ
／の性能低下を防止するシュラウド（１）を取付けるテ
ノン（２）からなっている。なお、図中（５）はレイン
フォース部である。そして、シュラウドは動翼の振動強
度を増すため等の、目的で装備されるが、蒸気タービン
の動翼が高速で回転すると、翼先端に設けられているシ
ュラウド（１）は、遠心力により変形する。特に高速回
転タービン又は翼間の間隔が長いタービンの動翼では、
シュラウドの遠心強度を増すために、従来のシュラウド
は頑丈になっているが、これに伴なって動翼及び翼根部
の遠心強度が大きいことが要求され、また、タービン運
転中に大きな応力が動翼及び翼根部に受けるため、Ｘ根
部に亀裂が生じることがあり、この亀裂は、シュラウド
の飛散を招き、重大な事故を生じる可能性もある。The rotor blade hole is the blade root part (4) embedded in the outer periphery of the disk.
The blade (3) receives the steam flowing out from the nozzle blade and generates rotational energy, and the steam flowing out from the nozzle blade flows into the gap between the outer periphery of the cleaner and the nozzle blade, reducing the performance of the steam turret. It consists of a tenon (2) to which a protective shroud (1) is attached. In addition, (5) in the figure is a reinforcement part. The shroud is installed for the purpose of increasing the vibration strength of the rotor blades, but when the rotor blades of a steam turbine rotate at high speed, the shroud (1) installed at the tip of the blade deforms due to centrifugal force. do. Particularly for high-speed rotating turbines or turbine blades with long spacing between blades,
In order to increase the shroud's centrifugal strength, conventional shrouds have become stronger, but this requires the rotor blades and blade roots to have greater centrifugal strength, and large stresses are applied during turbine operation. Due to the impact on the wing and the blade root, cracks may occur in the X root, and this crack may cause the shroud to fly off, resulting in a serious accident.

本発明は、上記従来の欠点を解消するものてあり、シュ
ラウドの重量を小さくし、タービン回転時のシュラ−ウ
ドの遠心力を減少し、従って羽根及び翼根部の応力を低
減することを目的とするものである。The present invention solves the above-mentioned conventional drawbacks, and aims to reduce the weight of the shroud, reduce the centrifugal force of the shroud during turbine rotation, and therefore reduce the stress on the blades and blade roots. It is something to do.

上記目的を達成するために本発明は、翼頂に２つのテノ
ンを有するタービン動翼において、１つのテノンは、前
方の動翼のテノンと短冊状シュララードで連結し、他の
１つのテノンは、後方の動翼のテノンと短冊状シュラウ
ドで連結するような千鳥状シュラウドに構成するもので
ある。In order to achieve the above object, the present invention provides a turbine rotor blade having two tenons at the top of the blade, one tenon is connected to the tenon of the front rotor blade by a strip-shaped shularade, and the other tenon is It has a staggered shroud that is connected to the tenon of the rear rotor blade by a strip-shaped shroud.

本発明の実施例を図面と共に説明する。Embodiments of the present invention will be described with reference to the drawings.

第３図及び第４図において、２つのテノン（２）　（２
）を有するタービン動翼（５）におい又、第３図に示す
ように、１つのテノン（２）は、前方の羽根（３′）の
テノン（２′）と短冊状シュラウド（１０ａ）で連結し
、他の１つのテノン（２）は後方の羽根（３”　）のテ
ノン（ｚ′Ｆ）と他の短冊状シュラウド（１０ｂ）で連
結する。In Figures 3 and 4, two tenons (2) (2
) In addition, as shown in Figure 3, one tenon (2) is connected to the tenon (2') of the front blade (3') by a strip-shaped shroud (10a). However, the other tenon (2) is connected to the tenon (z'F) of the rear vane (3'') by another strip-shaped shroud (10b).

革発明は、上記のように４１４成したので、第１図と第
３図を対比しても容易にわかるように、シュラウドの重
量を内幅に軽減できる。それゆえ、タービ／回転時のシ
ュラウドの遠心力が減少し、羽根及び翼根部の遠心応力
を減少させることができる。従って、羽根及び翼根部の
耐振動強度を増すことができる。Since the leather invention has been achieved as described above, the weight of the shroud can be reduced to the inner width, as can be easily seen by comparing FIGS. 1 and 3. Therefore, the centrifugal force of the shroud during turbine/rotation is reduced, and the centrifugal stress of the blades and blade roots can be reduced. Therefore, the vibration resistance strength of the blade and the blade root portion can be increased.

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

第１図は従来のタービン動翼の部分平面図、第２図は第
１図のルールからみた部分正面図、第３図は、本発明の
タービン動翼の平面図、第４図は、第３図のルールから
みた部分正面図である。 Ａ・・タービン動翼、２．２’ｌ、　　２”・・テノン
、３　、３１．３１１　＠横羽根、５・φレインフォー
ス部、１０ａ　、　１０ｂ−−シュラウド。 第１図 第２図 ／ＡFIG. 1 is a partial plan view of a conventional turbine rotor blade, FIG. 2 is a partial front view seen from the rules of FIG. 1, FIG. 3 is a plan view of the turbine rotor blade of the present invention, and FIG. 3 is a partial front view seen from the rules of FIG. 3. FIG. A... Turbine moving blade, 2.2'l, 2"... Tenon, 3, 31.311 @ side blade, 5 φ reinforcement part, 10a, 10b -- shroud. Fig. 1 Fig. 2/A

Claims (1)

【特許請求の範囲】[Claims] 翼頂に２つのテノンな有するタービン動翼において、１
つのテノンは前方の動翼のテノンと短冊状シュ２ウドで
連結し、他の１つのテノンは後方の動翼のテノンと短冊
状シュラウドで連結することを特徴とする千鳥型シュラ
ウド。In a turbine rotor blade with two tenons at the top of the blade, 1
A staggered shroud characterized in that one tenon is connected to the tenon of the forward moving blade by a rectangular shroud, and the other tenon is connected to the tenon of the rear moving blade by a rectangular shroud.
JP2751882A 1982-02-24 1982-02-24 Shroud in turbine moving blade Pending JPS58144605A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2751882A JPS58144605A (en) 1982-02-24 1982-02-24 Shroud in turbine moving blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2751882A JPS58144605A (en) 1982-02-24 1982-02-24 Shroud in turbine moving blade

Publications (1)

Publication Number Publication Date
JPS58144605A true JPS58144605A (en) 1983-08-29

Family

ID=12223343

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2751882A Pending JPS58144605A (en) 1982-02-24 1982-02-24 Shroud in turbine moving blade

Country Status (1)

Country Link
JP (1) JPS58144605A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1803898A2 (en) * 2002-01-28 2007-07-04 Kabushiki Kaisha Toshiba Geothermal turbine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1803898A2 (en) * 2002-01-28 2007-07-04 Kabushiki Kaisha Toshiba Geothermal turbine
EP1803898A3 (en) * 2002-01-28 2012-01-04 Kabushiki Kaisha Toshiba Geothermal turbine

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