JPS5925094B2 - gas turbine - Google Patents

gas turbine

Info

Publication number
JPS5925094B2
JPS5925094B2 JP56130145A JP13014581A JPS5925094B2 JP S5925094 B2 JPS5925094 B2 JP S5925094B2 JP 56130145 A JP56130145 A JP 56130145A JP 13014581 A JP13014581 A JP 13014581A JP S5925094 B2 JPS5925094 B2 JP S5925094B2
Authority
JP
Japan
Prior art keywords
shank
gas turbine
guide part
rotor
section
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.)
Expired
Application number
JP56130145A
Other languages
Japanese (ja)
Other versions
JPS5832906A (en
Inventor
昭紀 古閑
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.)
National Institute of Advanced Industrial Science and Technology AIST
Original Assignee
Agency of Industrial Science and Technology
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 Agency of Industrial Science and Technology filed Critical Agency of Industrial Science and Technology
Priority to JP56130145A priority Critical patent/JPS5925094B2/en
Publication of JPS5832906A publication Critical patent/JPS5832906A/en
Publication of JPS5925094B2 publication Critical patent/JPS5925094B2/en
Expired 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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
    • 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

Landscapes

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

Description

【発明の詳細な説明】 本発明はガスタービンに係り、特にタービン動翼のシャ
ンク部のシール性を向トさせるのに好適なガスタービン
に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a gas turbine, and more particularly to a gas turbine suitable for improving the sealing performance of a shank portion of a turbine rotor blade.

一般ニ、ガスタービンにおいて、タービンの冷却、また
はシールのために必要な空気を減らすことは、性能向と
のために重要であることは周知である。In general, it is well known that in gas turbines, reducing the amount of air required for cooling or sealing the turbine is important for improved performance.

そして、タービン動翼のシャンク部につｂても、シール
空気の減少を図るためにはシールを確実にすることが重
要となってくる。Also, in the shank portion of the turbine rotor blade, it is important to ensure a reliable seal in order to reduce the amount of seal air.

第１図は従来の一般的なガスタービンを示すもので、図
において１は静翼、２は動翼である。FIG. 1 shows a conventional general gas turbine. In the figure, 1 is a stationary blade and 2 is a rotor blade.

動翼２は植込部５を介してロータ４に植込まれている。The rotor blade 2 is implanted into the rotor 4 via an implant portion 5.

また動翼２の根元部にはシャンク部３が形成されている
。Further, a shank portion 3 is formed at the root portion of the rotor blade 2 .

しかして、ロータ４を冷たい雰囲気に保つため、例えば
シール空気６が流され、主流ガスγの混入を防止してい
る。In order to keep the rotor 4 in a cool atmosphere, for example, sealing air 6 is flowed to prevent the mainstream gas γ from entering.

しかしシャンク部３の部分の漏洩空気８が多くなると、
主流ガス１の混入が起こり危険となる。However, if the leakage air 8 in the shank part 3 increases,
Mainstream gas 1 may be mixed in, which is dangerous.

このため、前記漏洩空気８の量は最少限に抑える必要が
ある。For this reason, it is necessary to suppress the amount of the leaked air 8 to a minimum.

そこで、従来は第２図に示すように周方向に隣接する相
互のシャンク部３側面の対向位置に溝１０をそれぞれ設
け、この溝１０内に帯板状のシール板９を挿入する方法
を採っている。Therefore, conventionally, as shown in FIG. 2, grooves 10 are provided at opposing positions on the side surfaces of mutually adjacent shank portions 3 in the circumferential direction, and a band-shaped seal plate 9 is inserted into these grooves 10. ing.

しかしながら、この方法では互いに隣接するシャンク部
３がロータ４の軸方向に相対的に移動した場合には充分
なシール性を確保することが困難となる虞れがある他、
シール板９にせん断力が働いてシール板９が破損する懸
念がある。However, in this method, if the shank portions 3 adjacent to each other move relative to each other in the axial direction of the rotor 4, it may be difficult to ensure sufficient sealing performance.
There is a concern that the seal plate 9 may be damaged due to shearing force acting on the seal plate 9.

不発明はかかる従来の問題点を解決するためになされた
もので その目的とするところは、周方向に隣接するシ
ャンク部同士が相対的に移動しても充分なシール性を確
保することができ、しかもシール部材の破損する心配の
ないガスタービンを提供するにある。The invention was made to solve these conventional problems, and its purpose is to ensure sufficient sealing performance even if circumferentially adjacent shank parts move relative to each other. Moreover, it is an object of the present invention to provide a gas turbine in which there is no fear that the seal member will be damaged.

本発明はシャンク部側面に隣接する他の動翼のシャンク
部側面に略直角に対向し、ロータ中心を通るラジアル線
に対して一定の角度をもって底面の北端、ないしその延
長線が交差するように断面矩形の案内部を形成し、この
案内部に案内部底面にその背面を当接したときにシール
面がシャンク部側面と路面−となるように断面矩形のシ
ール部材をしゆう動自在に設けたことを特徴とするもの
である。The present invention is arranged so that the blade faces the side surface of the shank portion of another rotor blade adjacent to the side surface of the shank portion at a substantially right angle, and the north end of the bottom surface or its extension intersects at a certain angle with respect to the radial line passing through the center of the rotor. A guide part with a rectangular cross section is formed, and a seal member with a rectangular cross section is movably provided on the guide part so that the sealing surface is between the side surface of the shank part and the road surface when the back surface of the guide part is brought into contact with the bottom surface of the guide part. It is characterized by:

以下、本発明の一実施例を第３図および第４図を参照し
て説明する。An embodiment of the present invention will be described below with reference to FIGS. 3 and 4.

第３図および第４図において、符号２はシャンク部３を
備えた動翼であって、この動翼２を周方向に連ねてガス
タービンの段落が構成されている。In FIGS. 3 and 4, reference numeral 2 denotes a rotor blade having a shank portion 3, and the rotor blades 2 are connected in a circumferential direction to form a stage of a gas turbine.

シャンク部３の一側には隣接する他の動翼２のシャンク
部３の側面にほぼ直角に対向している断面矩形の案内部
１１が形成され（第４図参照）、その底面はロータ中心
を通るラジアル線Ｒに対して角度θだけ傾むけられてい
る。A guide part 11 having a rectangular cross section is formed on one side of the shank part 3 and faces the side surface of the shank part 3 of another adjacent rotor blade 2 at a substantially right angle (see FIG. 4), and its bottom surface is located at the center of the rotor. It is inclined at an angle θ with respect to a radial line R passing through the radial line R.

（第３図参照）また、この案内部１１には断面矩形のシ
ール片１２が装着されている。(See FIG. 3) Further, a seal piece 12 having a rectangular cross section is attached to this guide portion 11.

しかして、このシール片１２はタービン静止時にはシー
ル面つまり隣接する他の動翼２のシャンク部３に当接さ
れる面の反対側、すなわち背面側を案内部１１の底面に
押付けたときにシャンク部３の側面と前記シール面とが
ほぼ面一となるように形成され、したがってタービン運
転中を通してシール片１１は遠心力の周方向分力により
隣接するシャンク部３の側面にそのシール面が押付けら
れるようになっている。Therefore, when the turbine is stationary, this seal piece 12 is pressed against the bottom surface of the guide portion 11 with its seal surface, that is, the side opposite to the surface that abuts the shank portion 3 of the adjacent rotor blade 2, that is, the back side. The side surface of the portion 3 and the sealing surface are formed to be substantially flush with each other, and therefore, throughout the turbine operation, the sealing surface of the sealing piece 11 is pressed against the side surface of the adjacent shank portion 3 due to the circumferential component of centrifugal force. It is now possible to

本発明は上記のように構成されており、互いに隣接する
シャンク部３同士が周方向（入方向）に相対移動しても
シール片１１自体は隣接するシャンク部３の動きに追従
して動くため、シャンク部３の側面との間に隙間は生れ
ず、充分なシール性が保たれる。The present invention is configured as described above, and even if the adjacent shank portions 3 move relative to each other in the circumferential direction (input direction), the seal piece 11 itself moves following the movement of the adjacent shank portions 3. There is no gap between the shank portion 3 and the side surface of the shank portion 3, and sufficient sealing performance is maintained.

一方、シャンク部３同士が軸方向（Ｂ方向）に相対移動
する場合にはシール片１２もこれにつられて隣接するシ
ャンク部３と相対的に移動するが、この間シール片１２
のシール面は隣接スるシャンク部３の側面に密着したま
まであり、何らシール性は損なわれない。On the other hand, when the shank parts 3 move relative to each other in the axial direction (direction B), the seal piece 12 also moves relative to the adjacent shank part 3.
The sealing surface remains in close contact with the side surface of the adjacent shank portion 3, and the sealing performance is not impaired in any way.

そして、シャンク部３同士のこれらの周方向、ならびに
軸方向の相対的な移動の間を通じてシール片１２には遠
心力以外のシール片１２の動きを拘束するような力が作
用しないので、シール片１２ばそれ自身の遠心力で破損
しないように必要な強度を持たせておけば、何ら破損の
心配のないものである。During the relative movement of the shank portions 3 in the circumferential and axial directions, no force other than centrifugal force that restrains the movement of the seal piece 12 acts on the seal piece 12. 12. If it has the necessary strength so that it will not be damaged by its own centrifugal force, there is no need to worry about damage.

これらに加えてシール片１２を一方の動翼２のシャンク
部３に設けた案内部１１により支持する本発明は隣接す
るシャンク部３には何らの加工を施こす必要がなぐ、加
工の容易性の面において格段に有利である。In addition to these, the present invention in which the seal piece 12 is supported by the guide part 11 provided on the shank part 3 of one of the rotor blades 2 has the advantage that there is no need to perform any processing on the adjacent shank part 3, making it easy to process. It is extremely advantageous in this respect.

なお、上記実施例はシール片１２のシール面を相対する
シャンク部３の側面に合わせて平らな形に形成したもの
であるが、シール性についてより確実さを求められる場
合には例えば第５図に示されるようにシール片１３のシ
ール面を鋸刃状としても良い。In the above embodiment, the sealing surface of the sealing piece 12 is formed in a flat shape to match the side surface of the opposing shank portion 3, but if more reliable sealing performance is required, for example, the sealing surface of the sealing piece 12 shown in FIG. The sealing surface of the sealing piece 13 may have a sawtooth shape as shown in FIG.

また、遠心力のみではシール性を確保するのがやや困難
と思われる場合、次の方法を採用することにより確実な
ものとなる。Furthermore, if it seems difficult to ensure sealing performance using centrifugal force alone, it can be ensured by adopting the following method.

すなわち、第６図および第１図に示されるように案内部
１４に挿入されたシール片１５のシール面は隣接するシ
ャンク部３の側面にスプリング１６の反撥力により押付
けられる。That is, as shown in FIGS. 6 and 1, the seal surface of the seal piece 15 inserted into the guide portion 14 is pressed against the side surface of the adjacent shank portion 3 by the repulsive force of the spring 16.

ここで、符号１７は斜孔、１８はピンをそれぞれ示して
いる。Here, reference numeral 17 indicates a diagonal hole, and 18 indicates a pin.

本実施例におけるシール性はスプリング１６の反傍力に
より、常に一定に保たれること、また、シール片１５の
破損の生じ難いこと、さらには加工精度についてもそれ
程高いものを要求されないことは上記実施例における説
明から容易に理解されるとおりである。As mentioned above, the sealing performance in this embodiment is always kept constant due to the counterforce of the spring 16, the seal piece 15 is unlikely to be damaged, and the processing accuracy is not required to be very high. This is easily understood from the description in the examples.

以上本発明を好適な実施例により説明したが、本発明に
よれば周方向に隣接するシャンク部同士が相対的に移動
しても充分なシール性を確保することができる他、シー
ル部材の破損する心配のないものであり、有用性におい
て極めて優れている。The present invention has been described above with reference to preferred embodiments. According to the present invention, sufficient sealing performance can be ensured even if circumferentially adjacent shanks move relative to each other, and the sealing member can be damaged. There is no need to worry about this happening, and it is extremely useful.

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

第１図は従来のガスタービンの段落構成を示す断面図、
第２図は第１図の■−■線に沿う断面図、第３図は本発
明の要部を示す断面図、第４図は第３図のＩ’Ｖ−ＩＶ
線に沿う断面図、第５図は本発明の他の実施例を示す断
面図、第６図は本発明のさらに異なる実施例を示す断面
図、第７図は第６図の■−■線に沿う断面図である。 ２・・・動翼、３・・・シャンク部、ＩＬ１４・・・案
内部、１２，１３，１５・・・シール片、１６・・・ス
プリング、１γ・・・斜孔、１８・・・ピン。Figure 1 is a sectional view showing the stage configuration of a conventional gas turbine;
2 is a sectional view taken along the line ■-■ in FIG. 1, FIG. 3 is a sectional view showing the main parts of the present invention, and FIG.
5 is a sectional view showing another embodiment of the present invention, FIG. 6 is a sectional view showing still another embodiment of the present invention, and FIG. 7 is a sectional view taken along the line ■-■ of FIG. 6. FIG. 2... Moving blade, 3... Shank part, IL14... Guide part, 12, 13, 15... Seal piece, 16... Spring, 1γ... Diagonal hole, 18... Pin .

Claims (1)

【特許請求の範囲】[Claims] １ 周方向に隣接する動翼のシャンク部間にシール部材
を介装し、これによりシール空気が前記シャンク部間の
隙間を通って下流側に吸引されるのを防止するようにし
たガスタービンにおいて、前記シャンク部側面に隣接す
る他の動翼のシャンク部側面に略直角に対向し、ロータ
中心を通るラジアル線に対して一定の角度をもって底面
の北端、ないしその延長線が交差するように断面矩形の
案内部を形成し、この案内部に案内部底面にその背面乞
当接したときにンニル面が前記シャンク部側面と略同−
となるように断面矩形のシール部材をしゆう動自在に設
けたことを特徴とするガスタービン。1. In a gas turbine in which a sealing member is interposed between the shank portions of rotor blades adjacent in the circumferential direction, thereby preventing seal air from being sucked downstream through the gap between the shank portions. , a cross section that faces the side surface of the shank portion of another rotor blade adjacent to the side surface of the shank portion at a substantially right angle, and has a cross section such that the north end of the bottom surface or its extension line intersects at a certain angle with respect to a radial line passing through the center of the rotor. A rectangular guide part is formed, and when the back side of the guide part comes into contact with the bottom surface of the guide part, the inner surface is approximately the same as the side surface of the shank part.
A gas turbine characterized in that a seal member having a rectangular cross section is movably provided.
JP56130145A 1981-08-21 1981-08-21 gas turbine Expired JPS5925094B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP56130145A JPS5925094B2 (en) 1981-08-21 1981-08-21 gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP56130145A JPS5925094B2 (en) 1981-08-21 1981-08-21 gas turbine

Publications (2)

Publication Number Publication Date
JPS5832906A JPS5832906A (en) 1983-02-26
JPS5925094B2 true JPS5925094B2 (en) 1984-06-14

Family

ID=15027042

Family Applications (1)

Application Number Title Priority Date Filing Date
JP56130145A Expired JPS5925094B2 (en) 1981-08-21 1981-08-21 gas turbine

Country Status (1)

Country Link
JP (1) JPS5925094B2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
US6431825B1 (en) * 2000-07-28 2002-08-13 Alstom (Switzerland) Ltd Seal between static turbine parts

Also Published As

Publication number Publication date
JPS5832906A (en) 1983-02-26

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