JP5579112B2 - Turbine blade fixed structure and blade root spring removal method - Google Patents

Turbine blade fixed structure and blade root spring removal method Download PDF

Info

Publication number
JP5579112B2
JP5579112B2 JP2011070812A JP2011070812A JP5579112B2 JP 5579112 B2 JP5579112 B2 JP 5579112B2 JP 2011070812 A JP2011070812 A JP 2011070812A JP 2011070812 A JP2011070812 A JP 2011070812A JP 5579112 B2 JP5579112 B2 JP 5579112B2
Authority
JP
Japan
Prior art keywords
blade
blade root
groove
root spring
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.)
Expired - Fee Related
Application number
JP2011070812A
Other languages
Japanese (ja)
Other versions
JP2012202391A (en
Inventor
昌則 藤岡
博彦 伊藤
高彰 長川
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 JP2011070812A priority Critical patent/JP5579112B2/en
Publication of JP2012202391A publication Critical patent/JP2012202391A/en
Application granted granted Critical
Publication of JP5579112B2 publication Critical patent/JP5579112B2/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/505—Shape memory behaviour

Description

本発明は、タービン動翼の翼根部が嵌合される翼溝に当該翼根部を付勢して固定するタービン動翼の固定構造及び翼根部を付勢して前記翼溝に押し付ける翼根バネの脱着方法に関する。   The present invention relates to a turbine blade fixing structure that urges and fixes a blade root to a blade groove to which a blade root of a turbine blade is fitted, and a blade root spring that urges and presses the blade root against the blade groove. Relates to the method of desorption.

回転機械である蒸気タービンやガスタービンのタービン動翼は、ロータの翼溝にタービン動翼の翼根部を嵌め合わせることによりロータに固定されている。この嵌合構造では、翼溝と翼根部との間に、製造公差等による隙間が存在する。このような隙間があっても、ロータが高速で回転しているときには、タービン動翼に作用する遠心力によってタービン動翼がロータに固定されるので、タービン動翼が振動することはない。しかし、遠心力が低下するロータの低速回転時又は停止時にはタービン動翼が径方向に振動して、翼根部や翼溝の表面に傷をつけるおそれがある。また、この振動はタービン動翼の先端に取り付けられているシュラウドを介して伝達されて隣接するタービン動翼を損傷させる場合もある。そして、これらの損傷が著しい場合には、タービン動翼やロータの交換が必要となる場合もある。   A turbine blade of a steam turbine or a gas turbine, which is a rotating machine, is fixed to the rotor by fitting the blade root of the turbine blade into the blade groove of the rotor. In this fitting structure, there is a gap due to manufacturing tolerance or the like between the blade groove and the blade root. Even if there is such a gap, when the rotor is rotating at high speed, the turbine blade is not vibrated because the turbine blade is fixed to the rotor by the centrifugal force acting on the turbine blade. However, when the rotor is rotated at low speed or stopped when the centrifugal force is reduced, the turbine rotor blades may vibrate in the radial direction, which may damage the blade roots or the surfaces of the blade grooves. In addition, this vibration may be transmitted through a shroud attached to the tip of the turbine blade and damage adjacent turbine blades. And when these damages are remarkable, replacement | exchange of a turbine rotor blade or a rotor may be needed.

そこで、例えば、特許文献１には、タービン動翼の振動防止を目的として、複数の湾曲部を有する翼根バネが開示されている。図９は、翼根バネを、翼根部の翼溝側先端面と翼溝の底面との間の隙間（以下、溝隙間という）内に設置した状態を示す図である。
図９に示すように、翼根バネ３１は、中間部３３と、端部３２Ａ、３２Ｂと、から構成されており、この中間部３３が翼根部２１に密着するように設けられている。そして、翼根バネ３１の強力な押付力を利用して翼根部２１を翼溝１１に押し付けることによって、タービン動翼２０をタービンロータ１０に固定して振動を防止している。 Therefore, for example, Patent Document 1 discloses a blade root spring having a plurality of curved portions for the purpose of preventing vibration of the turbine rotor blade. FIG. 9 is a view showing a state in which the blade root spring is installed in a gap (hereinafter referred to as a groove gap) between the blade groove side tip surface of the blade root part and the bottom surface of the blade groove.
As shown in FIG. 9, the blade root spring 31 includes an intermediate portion 33 and end portions 32 </ b> A and 32 </ b> B. The intermediate portion 33 is provided so as to be in close contact with the blade root portion 21. Then, by using the strong pressing force of the blade root spring 31 to press the blade root portion 21 against the blade groove 11, the turbine rotor blade 20 is fixed to the turbine rotor 10 to prevent vibration.

また、タービン動翼の振動防止を目的とするものではないが、特許文献２には、タービン静止時のタービン動翼の固有振動数を測定する際に、タービン動翼の固定状態のばらつきを小さくする目的で押上バネによって、タービン動翼を押し上げて固定することが開示されている。この押上バネは、形状記憶合金製のコイルスプリングからなり、高温時（４０℃〜５０℃）には長さが短くなり、常温時には元の状態に戻る性質を有している。
押上バネを溝隙間内に挿入する際には、まず、押上バネを高温状態にして短くする。続いて、短い状態の押上バネを溝隙間内に挿入し、所定の位置に設置する。その後、押上バネの温度が低下して常温になると押上バネが元の状態に戻り、すなわち長くなり、タービン動翼を押し上げて固定する。このように押上バネによってタービン動翼を押し上げて固定することで、タービン動翼の固定状態のばらつきが小さくなるので、静止時のタービン動翼の固定振動数を正確に計測することができる。 Although not intended to prevent vibration of the turbine rotor blade, Patent Document 2 discloses that when measuring the natural frequency of the turbine rotor blade when the turbine is stationary, variation in the fixed state of the turbine rotor blade is reduced. For this purpose, it is disclosed that a turbine blade is pushed up and fixed by a push-up spring. This push-up spring is made of a coil spring made of a shape memory alloy and has a property that its length is shortened at a high temperature (40 ° C. to 50 ° C.) and returns to its original state at a normal temperature.
When the push-up spring is inserted into the groove gap, first, the push-up spring is shortened to a high temperature state. Subsequently, the push-up spring in a short state is inserted into the groove gap and installed at a predetermined position. Thereafter, when the temperature of the push-up spring decreases to normal temperature, the push-up spring returns to its original state, that is, becomes longer, and pushes and fixes the turbine rotor blade. In this way, by pushing up and fixing the turbine blade by the push-up spring, the variation in the fixed state of the turbine blade is reduced, so that the stationary frequency of the stationary turbine blade can be accurately measured.

特開２００５−２７３６４６号公報JP 2005-273646 A 特開平１−２３７３０４号公報JP-A-1-237304

しかしながら、特許文献１に記載の翼根バネは、繰り返し荷重によるへたりや経年的使用による変形によって押付力が低下するおそれがあるため、タービンの定期点検時に適宜交換される。
交換作業では、棒状の治具を溝隙間内に挿入して翼根バネの端面に当接させ、そのまま治具を溝隙間の長手方向に沿って押し込むことにより、翼根バネを溝隙間の外へ押し出している。ところが、翼根バネの押付力は強力なので、翼根バネを治具で押し出すのに非常に大きな力が必要になり、時には、治具をハンマーで叩いたり、油圧ジャッキで押し出したりして翼根バネを溝隙間の外へ押し出すこともある。
また、点検後に、新たな翼根バネを溝隙間内に取り付ける際も、翼根バネの押付力が作用するので、取り外す際と同様に、翼根バネの端面に治具を当接させ、治具をハンマーで叩いたり、油圧ジャッキで押したりしながら翼根バネを溝隙間内に挿入する場合がある。
したがって、翼根バネを脱着する作業は、手間がかかるうえに困難なので長い作業時間を要する。
また、翼根バネにハンマーで衝撃を加えたり、油圧ジャッキで強大な荷重を付与したりすると、翼根バネに接している翼根部や翼溝に傷をつけてしまうおそれがある。 However, the blade root spring described in Patent Document 1 may be appropriately replaced at the time of periodic inspection of the turbine because the pressing force may decrease due to sag due to repeated loads or deformation due to aging.
In the replacement work, a rod-shaped jig is inserted into the groove gap and brought into contact with the end face of the blade root spring, and the jig is pushed in the longitudinal direction of the groove gap to remove the blade root spring from the groove gap. Pushing out. However, since the pressing force of the blade root spring is strong, a very large force is required to push out the blade root spring with a jig, and sometimes the blade root spring is struck with a hammer or pushed out with a hydraulic jack. The spring may be pushed out of the groove gap.
Also, when a new blade root spring is installed in the groove gap after inspection, the pressing force of the blade root spring acts, so that a jig is brought into contact with the end surface of the blade root spring to remove it. The blade root spring may be inserted into the groove gap while hitting the tool with a hammer or pushing with a hydraulic jack.
Therefore, since the work for removing and attaching the blade root spring is time-consuming and difficult, a long work time is required.
Further, if an impact is applied to the blade root spring with a hammer or a strong load is applied with a hydraulic jack, the blade root portion or blade groove in contact with the blade root spring may be damaged.

なお、特許文献２に記載の押上バネは、そもそもタービン静止時の固定振動数の測定を目的としており、タービン静止時のみに装着されるものであって、タービン運転中にタービン動翼の振動を防止する、いわゆる翼根バネではない。   The push-up spring described in Patent Document 2 is originally intended to measure the fixed frequency when the turbine is stationary, and is mounted only when the turbine is stationary. It is not a so-called blade root spring to prevent.

そこで、本発明は、タービン動翼の翼根部及びロータの翼溝を傷つけることなく、短時間で翼根バネを交換可能なタービン動翼の固定構造及び翼根バネの脱着方法を提供することを目的とするものである。   Accordingly, the present invention provides a turbine rotor blade fixing structure and a blade root spring attaching / detaching method capable of replacing the blade root spring in a short time without damaging the blade root of the turbine rotor blade and the blade groove of the rotor. It is the purpose.

上述した課題を解決する本発明に係るタービン動翼の固定構造は、タービン動翼の翼根部を翼溝に嵌合して固定するタービン動翼の固定構造であって、
線状部材をコイル状に巻いて形成され、前記翼根部と前記翼溝との間の隙間内に設けられる翼根バネを備え、
前記翼根バネは、外周面が前記翼根部の先端面と前記翼溝の底面とに接触するように、前記隙間の長手方向に沿って配置され、
前記翼根バネの径方向の自然長は、前記翼根部と前記翼溝との間の隙間よりも長いことを特徴とする。
上記タービン動翼の固定構造によれば、線状部材をコイル状に巻いた翼根バネが隙間内に設けられているので、翼根バネをその長手方向に引っ張ることで、翼根バネが縮径して隙間の長さよりも短くした後に、タービン動翼及び翼根バネをそれぞれ翼溝に対して脱着するので、翼根部や翼溝に傷をつけることなく、短時間で容易に翼根バネの脱着作業を実施できる。
なお、本明細書では、翼根バネの径方向の自然長とは、荷重がかかっていないときの翼根バネの外径を意味する。 A turbine rotor blade fixing structure according to the present invention that solves the above-described problem is a turbine rotor blade fixing structure that fits and fixes a blade root portion of a turbine rotor blade into a blade groove,
It is formed by winding a linear member in a coil shape, and includes a blade root spring provided in a gap between the blade root portion and the blade groove,
The blade root spring is disposed along the longitudinal direction of the gap so that the outer peripheral surface contacts the tip surface of the blade root portion and the bottom surface of the blade groove,
The radial length of the blade root spring is longer than the gap between the blade root and the blade groove.
According to the turbine rotor blade fixing structure, since the blade root spring in which the linear member is wound in a coil shape is provided in the gap, the blade root spring is contracted by pulling the blade root spring in the longitudinal direction. After the diameter is made shorter than the length of the gap, the turbine rotor blade and blade root spring are detached from the blade groove, so that the blade root spring can be easily and quickly removed without damaging the blade root or blade groove. Desorption work can be carried out.
In the present specification, the radial natural length of the blade root spring means the outer diameter of the blade root spring when no load is applied.

また、前記翼根バネの長手方向における中央部と該中央部の両端に位置する両端部とは、前記両端部の径方向の自然長が前記中央部の径方向の自然長よりも小さくなるように構成されていてもよい。
上記翼根バネによれば、両端部の径方向の自然長が中央部の径方向の自然長よりも小さいため、径方向の自然長の長さが長手方向の全長にわたって一様な翼根バネよりも、端部を隙間の外に取り出し易く、翼根バネを引っ張る作業を容易に実施することができる。
また、上記翼根バネによれば、両端部の径方向の自然長が中央部の径方向の自然長よりも小さいので、径方向の自然長の長さが長手方向の全長にわたって一様な翼根バネを用いた場合よりも容易に隙間内へ挿入することができる。 In addition, the central portion in the longitudinal direction of the blade root spring and the both end portions located at both ends of the central portion are such that the natural length in the radial direction of the both end portions is smaller than the natural length in the radial direction of the central portion. It may be configured.
According to the blade root spring, since the natural length in the radial direction at both ends is smaller than the natural length in the radial direction at the central portion, the length of the natural length in the radial direction is uniform over the entire length in the longitudinal direction. As a result, the end portion can be easily taken out of the gap, and the operation of pulling the blade root spring can be easily performed.
Further, according to the blade root spring, since the natural length in the radial direction at both ends is smaller than the natural length in the radial direction at the central portion, the length of the natural length in the radial direction is uniform over the entire length in the longitudinal direction. It can be inserted into the gap more easily than when a root spring is used.

また、前記線状部材は、複数の線状体を撚って形成されていてもよい。
上記線状部材によれば、複数の線状体から形成されているので、線状体の撚りをほぐして線状部材をばらばらにし、翼根バネのコイル形状を変形させて翼根バネの復元力を無くすことにより、翼根バネを隙間内から引き出す際に翼根部や翼溝に傷をつけない。 The linear member may be formed by twisting a plurality of linear bodies.
According to the linear member, since the linear member is formed from a plurality of linear members, the linear member is separated by loosening the twist of the linear member, and the coil shape of the blade root spring is deformed to restore the blade root spring. By eliminating the force, the blade root part and the blade groove are not damaged when the blade root spring is pulled out from the gap.

また、本発明に係る翼根バネの脱着方法は、タービン動翼の翼根部と該翼根部が嵌合される翼溝との間に形成された隙間に設けられ、前記翼根部を付勢して前記翼溝に押し付ける翼根バネの脱着方法であって、
前記隙間の長手方向に沿って前記翼根バネに引張荷重を作用させて、前記長手方向と直交する方向の前記翼根バネの長さを縮径させる縮径工程と、
前記翼根バネが縮径された状態で、前記タービン動翼を前記翼溝に対して脱着するタービン動翼脱着工程と、
前記タービン動翼が取り外された状態で、前記翼根バネを前記翼溝に対して脱着する翼根バネ脱着工程と、
を備えることを特徴とする。
上記翼根バネの脱着方法によれば、隙間内に設けられている翼根バネを隙間の長手方向に引っ張ることで、隙間の長手方向と直交する方向の翼根バネの長さを縮径して隙間の長さよりも短くした後に、タービン動翼及び翼根バネをそれぞれ翼溝に対して脱着するので、翼根部や翼溝に傷をつけることなく、短時間で容易に翼根バネの脱着作業を実施できる。 The blade root spring attaching / detaching method according to the present invention is provided in a gap formed between a blade root portion of a turbine blade and a blade groove into which the blade root portion is fitted, and biases the blade root portion. A method of removing and attaching the blade root spring pressed against the blade groove,
A diameter reducing step of reducing the length of the blade root spring in a direction orthogonal to the longitudinal direction by applying a tensile load to the blade root spring along the longitudinal direction of the gap;
A turbine rotor blade attaching / detaching step of attaching / detaching the turbine rotor blade to / from the blade groove with the blade root spring having a reduced diameter;
A blade root spring detaching step of detaching the blade root spring with respect to the blade groove in a state where the turbine rotor blade is removed;
It is characterized by providing.
According to the above-described method for attaching and detaching the blade root spring, the blade root spring provided in the gap is pulled in the longitudinal direction of the gap, thereby reducing the length of the blade root spring in the direction perpendicular to the longitudinal direction of the gap. Since the turbine blade and blade root spring are detached from the blade groove after making it shorter than the gap length, the blade root spring can be easily detached in a short time without damaging the blade root or blade groove. Can perform work.

また、前記タービン動翼を前記翼溝に対して脱着した後に、前記縮径された前記翼根バネに作用している前記引張荷重を解放してもよい。
上記タービン動翼を翼溝に対して脱着した後に、引張荷重を解放すると翼根バネが拡径し、タービン動翼の翼根部を付勢して翼溝に押し付けることができる。 The tensile load acting on the reduced diameter blade root spring may be released after the turbine rotor blade is detached from the blade groove.
When the tensile load is released after detaching the turbine blade from the blade groove, the blade root spring expands, and the blade root portion of the turbine blade can be urged and pressed against the blade groove.

また、本発明に係る翼根バネの脱着方法は、タービン動翼の翼根部と該翼根部が嵌合される翼溝との間に形成された隙間に設けられ、前記翼根部を付勢して前記翼溝に押し付ける翼根バネの脱着方法であって、
前記隙間の長手方向に沿って前記翼根バネに引張荷重を作用させて、前記長手方向と直交する方向の前記翼根バネの長さを縮径させる第２縮径工程と、
前記タービン動翼が前記翼溝に取り付けられた状態で、前記縮径された前記翼根バネを前記隙間に対して脱着する第２翼根バネ脱着工程と、
を備えることを特徴とする。
上記翼根バネの脱着方法によれば、隙間内に設けられている翼根バネを隙間の長手方向に引っ張ることで、隙間の長手方向と直交する方向の翼根バネの長さを縮径して隙間の長さよりも短くした後に、翼根バネを隙間に対して脱着するので、翼根部や翼溝に傷をつけることなく、短時間で容易に翼根バネの脱着作業を実施できる。 The blade root spring attaching / detaching method according to the present invention is provided in a gap formed between a blade root portion of a turbine blade and a blade groove into which the blade root portion is fitted, and biases the blade root portion. A method of removing and attaching the blade root spring pressed against the blade groove,
A second diameter reducing step of reducing the length of the blade root spring in a direction orthogonal to the longitudinal direction by applying a tensile load to the blade root spring along the longitudinal direction of the gap;
A second blade root spring detaching step of detaching the reduced diameter blade root spring with respect to the gap in a state where the turbine rotor blade is attached to the blade groove;
It is characterized by providing.
According to the above-described method for attaching and detaching the blade root spring, the blade root spring provided in the gap is pulled in the longitudinal direction of the gap, thereby reducing the length of the blade root spring in the direction perpendicular to the longitudinal direction of the gap. Since the blade root spring is detached from the gap after the gap is made shorter than the length of the gap, the blade root spring can be easily attached and detached in a short time without damaging the blade root part or the blade groove.

本発明によれば、タービン動翼の翼根部や翼溝を傷つけることなく翼根バネを短時間で脱着することができる。   According to the present invention, the blade root spring can be detached in a short time without damaging the blade root portion or blade groove of the turbine rotor blade.

本発明の実施形態に係るタービン動翼をタービンロータに接続した状態を示す斜視図である。It is a perspective view which shows the state which connected the turbine rotor blade which concerns on embodiment of this invention to the turbine rotor. 翼根バネの側面図である。It is a side view of a blade root spring. 図２のＡ矢視図である。FIG. 3 is a view as seen from an arrow A in FIG. 2. 翼根部の翼溝側先端面と翼溝の底面との間の溝隙間に翼根バネを設けた状態を示す拡大断面図である。FIG. 6 is an enlarged cross-sectional view showing a state in which a blade root spring is provided in a groove gap between the blade groove tip end surface of the blade root portion and the bottom surface of the blade groove. 図４のＢ−Ｂ断面図である。It is BB sectional drawing of FIG. 翼根バネを溝隙間内から取り外している状態を示す概略図である。It is the schematic which shows the state which has removed the blade root spring from the inside of a groove gap. 図６のＣ−Ｃ断面図である。It is CC sectional drawing of FIG. 翼根バネを溝隙間内に取り付けている状態を示す概略図である。It is the schematic which shows the state which has attached the blade root spring in the groove clearance. タービンロータの翼溝とタービン動翼の翼根部との溝隙間に従来の翼根バネを設けた状態を示す断面図である。It is sectional drawing which shows the state which provided the conventional blade root spring in the groove clearance of the blade groove | channel of a turbine rotor, and the blade root part of a turbine rotor blade.

以下、本発明に係る回転機械の翼根バネの実施形態について図面を用いて詳細に説明する。なお、以下の説明では、翼根バネをガスタービンに適用した場合について説明するが、これに限定されるものではなく、蒸気タービンやジェットエンジン等のタービンにも適用することができる。加えて、ガスタービンやジェットエンジンの空気圧縮機等にも適用することができる。
また、以下の実施例に記載されている構成部品の寸法、材質、形状、その相対配置などは特に特定的な記載がない限り、この発明の範囲をそれのみに限定する趣旨ではなく、単なる説明例にすぎない。 Hereinafter, embodiments of a blade root spring of a rotating machine according to the present invention will be described in detail with reference to the drawings. In the following description, the case where the blade root spring is applied to a gas turbine will be described. However, the present invention is not limited to this and can be applied to a turbine such as a steam turbine or a jet engine. In addition, it can be applied to an air compressor of a gas turbine or a jet engine.
Further, the dimensions, materials, shapes, relative arrangements, and the like of the component parts described in the following examples are not intended to limit the scope of the present invention unless otherwise specified, and are merely explanations. It is just an example.

図１は、本発明の実施形態に係るタービン動翼をタービンロータに接続した状態を示す斜視図である。
図１に示すように、ガスタービン１のタービン動翼２０は、翼根部２１がタービンロータ１０に形成された翼溝１１に嵌合することにより、タービンロータ１０に固定されている。
タービンロータ１０の外周部には、周方向に所定の間隔で複数の翼溝１１が設けられている。各翼溝１１は、タービンロータ１０の軸方向に沿って開口されている。加えて、各翼溝１１には、タービンロータ１０の径方向に沿って凸部１２及び凹部１３が交互に複数設けられている。また、タービン動翼２０の翼根部２１には、凹部１３と係合する凸部２２と、凸部１２と係合する凹部２３とが交互に複数設けられている。
そして、翼溝１１の凸部１２に翼根部２１の凹部２３が嵌合するとともに、翼溝１１の凹部１３に翼根部２１の凸部２２が嵌合してタービン動翼２０がタービンロータ１０に接続される。
また、翼根部２１の翼溝側先端面２４と翼溝１１の底面１４との間の溝隙間には翼根バネが設けられており、この翼根バネによって翼根部２１は翼溝１１に押し付けられている。 FIG. 1 is a perspective view showing a state in which a turbine rotor blade according to an embodiment of the present invention is connected to a turbine rotor.
As shown in FIG. 1, the turbine rotor blade 20 of the gas turbine 1 is fixed to the turbine rotor 10 by fitting a blade root portion 21 into a blade groove 11 formed in the turbine rotor 10.
A plurality of blade grooves 11 are provided on the outer peripheral portion of the turbine rotor 10 at predetermined intervals in the circumferential direction. Each blade groove 11 is opened along the axial direction of the turbine rotor 10. In addition, a plurality of convex portions 12 and concave portions 13 are alternately provided in each blade groove 11 along the radial direction of the turbine rotor 10. Further, the blade root portion 21 of the turbine rotor blade 20 is provided with a plurality of convex portions 22 that engage with the concave portions 13 and a plurality of concave portions 23 that engage with the convex portions 12.
Then, the concave portion 23 of the blade root portion 21 is fitted to the convex portion 12 of the blade groove 11, and the convex portion 22 of the blade root portion 21 is fitted to the concave portion 13 of the blade groove 11, so that the turbine rotor blade 20 is attached to the turbine rotor 10. Connected.
Further, a blade root spring is provided in the groove gap between the blade groove side tip surface 24 of the blade root 21 and the bottom surface 14 of the blade groove 11, and the blade root 21 is pressed against the blade groove 11 by this blade root spring. It has been.

図２は、翼根バネの側面図である。また、図３は、図２のＡ矢視図である。
図２及び図３に示すように、翼根バネ３は、線状部材をコイル状（螺旋状）に巻いて形成され、本体部１５と、端部１６Ａ、１６Ｂを有している。
本体部１５は、その径方向の自然長Ｄ０が翼根部２１の翼溝側先端面２４と翼溝１１の底面１４との間の溝隙間の高さよりも大きくなるように形成されている。
端部１６Ａ、１６Ｂは、本体部１５の両側に延在するように設けられている。また、端部１６Ａ、１６Ｂは、その径方向の自然長Ｍ０が本体部１５の自然長Ｄ０よりも短くて、かつ、溝隙間の高さよりも短くなるように形成されている。
翼根バネ３の線状部材は、耐摩耗性及び耐熱性を有する材料であれば特に限定されないが、例えば、鋼線、銅線、チタン線等を用いることができる。
翼根バネ３の一端３４を固定して他端３５を引っ張ると、翼根バネ３はその長手方向に伸張するとともに径方向の長さが縮径する性質を有している。 FIG. 2 is a side view of the blade root spring. FIG. 3 is a view taken in the direction of arrow A in FIG.
As shown in FIGS. 2 and 3, the blade root spring 3 is formed by winding a linear member in a coil shape (spiral shape), and has a main body portion 15 and end portions 16A and 16B.
The main body 15 is formed so that its natural length D 0 in the radial direction is larger than the height of the groove gap between the blade groove side tip surface 24 of the blade root 21 and the bottom surface 14 of the blade groove 11.
The end portions 16 </ b> A and 16 </ b> B are provided so as to extend on both sides of the main body portion 15. The end portions 16A, 16B is shorter than the natural length D 0 of the main body portion 15 is a natural length M 0 in the radial direction, and is formed to be shorter than the height of the groove gap.
The linear member of the blade root spring 3 is not particularly limited as long as it is a material having wear resistance and heat resistance. For example, a steel wire, a copper wire, a titanium wire, or the like can be used.
When one end 34 of the blade root spring 3 is fixed and the other end 35 is pulled, the blade root spring 3 has a property of extending in the longitudinal direction and reducing the length in the radial direction.

図４は、翼根部２１の翼溝側先端面２４と翼溝１１の底面１４との間の溝隙間に翼根バネ３を設けた状態を示す拡大断面図である。また、図５は、図４のＢ−Ｂ断面図である。
図４及び図５に示すように、翼根バネ３は、溝隙間２内の長手方向に沿って設けられている。
本体部１５の径方向の自然長Ｄ０は溝隙間の高さＨよりも長いので、本体部１５は翼根部２１の翼溝側先端面２４及び翼溝１１の底面１４に密着している。また、端部１６Ａ、１６Ｂの径方向の自然長Ｍ０は溝隙間の高さＨよりも短いので、端部１６Ａ、１６Ｂと翼根部２１の翼溝側先端面２４との間には隙間が形成されている。このとき、翼根バネ３の本体部１５の押付力によって、翼根部２１はタービンロータ１０の径方向外方に付勢され、翼溝１１に押し付けられている。
溝隙間２の両端には、翼根バネ３の抜け出しを防止するためのキャップ４Ａ、４Ｂがそれぞれ設けられている。 FIG. 4 is an enlarged cross-sectional view showing a state in which the blade root spring 3 is provided in the groove gap between the blade groove side tip surface 24 of the blade root portion 21 and the bottom surface 14 of the blade groove 11. FIG. 5 is a sectional view taken along line BB in FIG.
As shown in FIGS. 4 and 5, the blade root spring 3 is provided along the longitudinal direction in the groove gap 2.
Since the natural length D 0 in the radial direction of the main body portion 15 is longer than the height H of the groove gap, the main body portion 15 is in close contact with the blade groove side tip surface 24 of the blade root portion 21 and the bottom surface 14 of the blade groove 11. Further, since the natural length M 0 in the radial direction of the end portions 16A and 16B is shorter than the height H of the groove gap, there is a gap between the end portions 16A and 16B and the blade groove side tip surface 24 of the blade root portion 21. Is formed. At this time, the blade root 21 is urged radially outward of the turbine rotor 10 by the pressing force of the main body 15 of the blade root spring 3 and is pressed against the blade groove 11.
Caps 4A and 4B are provided at both ends of the groove gap 2 to prevent the blade root spring 3 from coming out.

次に、翼根バネ３を翼溝１１内から取り外す方法について説明する。   Next, a method for removing the blade root spring 3 from the blade groove 11 will be described.

図６は、翼根バネ３を翼溝１１内から取り外している状態を示す概略図である。また、図７は、図６のＣ−Ｃ断面図である。
図６及び図７に示すように、まず、溝隙間２の両端に設けられているキャップ４Ａ、４Ｂを取り外す。
次に、溝隙間２内に設けられている翼根バネ３の両端３４、３５にそれぞれ治具５を掛け、両端３４、３５を引張方向（図６中の矢印方向）に引っ張る。両端３４、３５を引っ張ると、端部１６Ａ、１６Ｂが引張方向へ伸長しながらその径方向の長さＭ１が縮径し、続いて、本体部１５が伸長しながらその径方向の長さＤ１が縮径する。このとき、本体部１５の径方向の長さＤ１が溝隙間の高さＨよりも短くなるまで、すなわち、翼根バネ３が翼溝側先端面２４から離間するまで翼根バネ３の両端３４、３５を引っ張る。
そして、翼根バネ３を縮径させた状態のままで、タービン動翼２０の翼根部２１を溝隙間２の長手方向へ移動させて引き抜く。
翼根部２１を移動させても、翼根バネ３の本体部１５の径方向の長さＤ１は溝隙間２の高さＨよりも短いので、翼根バネ３に接触することはない。
その後、翼根バネ３を縮径させた状態のまま、翼根部２１が取り外された翼溝１１内から翼根バネ３を取り外す。なお、翼根バネ３の引張荷重を解放して翼根バネ３の長さを元の状態に戻し、その後、翼溝１１内から翼根バネ３を取り外してもよい。
これによって、翼根部２１及び翼溝１１を傷つけることなく、翼根バネ３を容易に取り外すことができる。 FIG. 6 is a schematic view showing a state in which the blade root spring 3 is removed from the blade groove 11. FIG. 7 is a cross-sectional view taken along the line CC of FIG.
As shown in FIGS. 6 and 7, first, caps 4A and 4B provided at both ends of the groove gap 2 are removed.
Next, the jig 5 is put on both ends 34 and 35 of the blade root spring 3 provided in the groove gap 2, and the both ends 34 and 35 are pulled in the pulling direction (arrow direction in FIG. 6). Pulling the ends 34 and 35, the end portion 16A, 16B is the length M 1 of the radial diameter while extending the pulling direction, followed by, in the radial direction while the main body portion 15 is extended in length D 1 is reduced in diameter. At this time, to a length D 1 of the radial direction of the main body portion 15 is shorter than the height H of the groove gap, i.e., both ends of the blade root spring 3 until the blade root spring 3 is separated from the blade groove side distal end surface 24 Pull 34 and 35.
Then, with the diameter of the blade root spring 3 being reduced, the blade root portion 21 of the turbine rotor blade 20 is moved in the longitudinal direction of the groove gap 2 and pulled out.
Even if the blade root portion 21 is moved, the radial length D 1 of the main body portion 15 of the blade root spring 3 is shorter than the height H of the groove gap 2, so that it does not contact the blade root spring 3.
Thereafter, the blade root spring 3 is removed from the blade groove 11 from which the blade root portion 21 has been removed, while the diameter of the blade root spring 3 is reduced. The blade root spring 3 may be removed from the blade groove 11 after the tensile load of the blade root spring 3 is released to return the length of the blade root spring 3 to its original state.
Thereby, the blade root spring 3 can be easily removed without damaging the blade root portion 21 and the blade groove 11.

次に、翼根バネ３を翼溝１１内に取り付ける方法について説明する。   Next, a method for mounting the blade root spring 3 in the blade groove 11 will be described.

図８は、翼根バネ３を溝隙間２内に取り付けている状態を示す概略図である。
図８に示すように、まず、翼根バネ３の両端３４、３５に治具５を掛け、両端３４、３５をそれぞれ引張方向に引っ張って、翼根バネ３を縮径させる。このとき、本体部１５の径方向の長さＤ１が溝隙間の高さＨよりも短くなるまで、両端３４、３５を引っ張る。
次に、縮径させた状態の翼根バネ３の本体部１５を翼溝１１内に設ける。また、両端３４、３５をそれぞれ翼溝１１の外に配置して、両端３４、３５間の翼根バネ３の長さが変わらないように保持する。翼溝１１内にタービン動翼２０の翼根部２１が無いので、翼根バネ３を容易に翼溝１１内に取り付けることができる。
次に、タービン動翼２０の翼根部２１を翼溝１１内に挿入して嵌合する。翼根部２１を翼溝１１内に挿入しても、翼根バネ３の径方向の長さＤ１は溝隙間２の高さＨよりも短いので、翼根バネ３に接触することはない。
その後、翼根バネ３の引っ張り力を徐々に解放し、翼根バネ３の長手方向の長さを収縮させる。翼根バネ３が収縮すると、翼根バネ３の径方向の長さＤ１が次第に長くなり、翼根部２１の翼溝側先端面２４をタービンロータ１０の径方向外方に付勢して翼溝１１に押し付けて固定する。
最後に、溝隙間２の両端にキャップ４Ａ、４Ｂを取り付ける。
したがって、翼根部２１及び翼溝１１を傷つけることなく、翼根バネ３を短時間で取り付けることができる。 FIG. 8 is a schematic view showing a state in which the blade root spring 3 is attached in the groove gap 2.
As shown in FIG. 8, first, the jig 5 is hung on both ends 34, 35 of the blade root spring 3, and both ends 34, 35 are pulled in the pulling direction to reduce the diameter of the blade root spring 3. In this case, the radial length D 1 of the main body portion 15 until shorter than the height H of the groove gap, pull the two ends 34, 35.
Next, the main body portion 15 of the blade root spring 3 in a reduced diameter state is provided in the blade groove 11. Further, both ends 34 and 35 are arranged outside the blade groove 11 and are held so that the length of the blade root spring 3 between the both ends 34 and 35 does not change. Since there is no blade root portion 21 of the turbine rotor blade 20 in the blade groove 11, the blade root spring 3 can be easily mounted in the blade groove 11.
Next, the blade root portion 21 of the turbine blade 20 is inserted into the blade groove 11 and fitted. Even when the blade root portion 21 is inserted into the blade groove 11, the radial length D 1 of the blade root spring 3 is shorter than the height H of the groove gap 2, so that it does not contact the blade root spring 3.
Thereafter, the tensile force of the blade root spring 3 is gradually released, and the length of the blade root spring 3 in the longitudinal direction is contracted. When the blade root spring 3 is contracted gradually it becomes longer radial length D 1 of the blade root spring 3 biases the blade groove side leading end surface 24 of the blade root portion 21 radially outward of the turbine rotor 10 and blades Press against the groove 11 and fix.
Finally, caps 4A and 4B are attached to both ends of the groove gap 2.
Therefore, the blade root spring 3 can be attached in a short time without damaging the blade root portion 21 and the blade groove 11.

上述したように、本実施形態における翼根バネ３の脱着方法によれば、溝隙間２内に設けられている翼根バネ３を長手方向に引っ張ることで、翼根バネ３を縮径して溝隙間２の高さＨよりも短くした後に、タービン動翼２０及び翼根バネ３をそれぞれ翼溝１１に対して脱着するので、翼根部２１や翼溝１１に傷をつけることがなく、短時間で容易に翼根バネ３の脱着作業を実施できる。   As described above, according to the method for attaching and detaching the blade root spring 3 in the present embodiment, the blade root spring 3 is reduced in diameter by pulling the blade root spring 3 provided in the groove gap 2 in the longitudinal direction. Since the turbine rotor blade 20 and the blade root spring 3 are respectively detached from the blade groove 11 after being made shorter than the height H of the groove gap 2, the blade root portion 21 and the blade groove 11 are not damaged. The detachment operation of the blade root spring 3 can be easily performed in time.

また、端部１６Ａ、１６Ｂと翼根部２１の翼溝側先端面２４との間には隙間が形成されているため、端部１６Ａ、１６Ｂをそれぞれ溝隙間２の外に取り出し易く、翼根バネ３を引っ張る作業を容易に実施することができる。   In addition, since gaps are formed between the end portions 16A, 16B and the blade groove side tip surface 24 of the blade root portion 21, the end portions 16A, 16B can be easily taken out of the groove gap 2, respectively, and the blade root spring The operation | work which pulls 3 can be implemented easily.

なお、本実施形態では、タービン動翼２０を嵌合していない翼溝１１に対して縮径された状態の翼根バネ３を脱着する場合について説明したが、これに限定されるものではなく、タービン動翼２０を嵌合している翼溝１１の溝隙間２に対して縮径された状態の翼根バネ３を脱着してもよい。具体的には、溝隙間２内に設けられている翼根バネ３を引張方向に引っ張って径方向の長さＤ１を縮径させて、タービン動翼２０が翼溝１１に嵌合した状態のままの溝隙間２内から翼根バネ３を引き抜いたり、溝隙間２内に翼根バネ３を挿入したりしてもよい。かかる場合によれば、翼根バネ３の本体部１５の径方向の長さＤ１よりも端部１６Ａ、１６Ｂの径方向の長さＭ１が短いので、翼根バネ３を溝隙間２内へ容易に挿入することができる。 In the present embodiment, the case where the blade root spring 3 in a state of being reduced in diameter with respect to the blade groove 11 not fitted with the turbine rotor blade 20 is described, but is not limited thereto. The blade root spring 3 in a state of being reduced in diameter relative to the groove gap 2 of the blade groove 11 into which the turbine rotor blade 20 is fitted may be detached. State Specifically, reduced in diameter in the radial direction of the length D 1 pulling direction tensile blade root spring 3 provided in the groove gap 2, the turbine blades 20 is fitted in the blade groove 11 The blade root spring 3 may be pulled out from the groove gap 2 as it is, or the blade root spring 3 may be inserted into the groove gap 2. According to such a case, the radial length D end 16A than the first body portion 15 of the blade root spring 3, the radial length M 1 of the 16B is short, the blade root spring 3 in the groove gap 2 Can be easily inserted into.

なお、翼根バネ３として、１本の線状部材をコイル状に巻いたものを用いた場合について説明したが、これに限定されるものではなく、線状部材を複数の線状体を撚り合わせて形成してもよい。線状体として、耐摩耗性及び耐熱性を有する金属線を用いるのが好ましく、例えば、鋼線、銅線、チタン線等を用いる。複数の線状体から形成された翼根バネの一端を固定して他端を引っ張ると、翼根バネはその長手方向に伸張するとともに径方向の長さＤ１、Ｍ１が縮径する性質を有しているため、上述した翼根バネ３と同様の脱着方法で翼溝１１内に脱着することができる。
特に、複数の線状体からなる翼根バネを翼溝１１内から取り外す場合においては、線状体の撚りをほぐして線状部材をばらばらにし、翼根バネのコイル形状を変形させて翼根バネの復元力を無くすことにより、翼根バネを翼溝１１内から取り外すことができる。 In addition, although the case where what wound the one linear member in the coil shape was used as the blade root spring 3 was demonstrated, it is not limited to this, A linear member is twisted by several linear bodies. You may form together. A metal wire having wear resistance and heat resistance is preferably used as the linear body, and for example, a steel wire, a copper wire, a titanium wire, or the like is used. When one end of a blade root spring formed from a plurality of linear bodies is fixed and the other end is pulled, the blade root spring expands in the longitudinal direction and the lengths D 1 and M 1 in the radial direction contract. Therefore, it can be detached into the blade groove 11 by the same removal method as the blade root spring 3 described above.
In particular, when a blade root spring composed of a plurality of linear bodies is removed from the blade groove 11, the linear members are separated by loosening the twist of the linear body, and the coil shape of the blade root spring is deformed to deform the blade root. By eliminating the restoring force of the spring, the blade root spring can be removed from the blade groove 11.

１ ガスタービン
２ 溝隙間
３ 翼根バネ
４Ａ、４Ｂ キャップ
５ 治具
１０ タービンロータ
１１ 翼溝
１２ 凸部
１３ 凹部
１４ 底面
１５ 本体部
１６Ａ 端部
１６Ｂ 端部
２０ タービン動翼
２１ 翼根部
２２ 凸部
２３ 凹部
２４ 翼溝側先端面
３１ 翼根バネ
３２Ａ 端部
３２Ｂ 端部
３３ 中間部
３４ 一端
３５ 他端
Ｈ 溝隙間の高さ
Ｄ０ 本体部の径方向の自然長
Ｄ１ 本体部の径方向の長さ
Ｍ０ 端部の径方向の自然長
Ｍ１ 端部の径方向の長さ DESCRIPTION OF SYMBOLS 1 Gas turbine 2 Groove clearance 3 Blade root spring 4A, 4B Cap 5 Jig 10 Turbine rotor 11 Blade groove 12 Convex part 13 Concave part 14 Bottom face 15 Main part 16A End part 16B End part 20 Turbine rotor blade 21 Blade root part 22 Convex part 23 Recess 24 Blade groove tip surface 31 Blade root spring 32A End portion 32B End portion 33 Intermediate portion 34 One end 35 Other end H Groove gap height D 0 Radial length of main body portion D 1 Radial length of main body portion M 0 Natural length in the radial direction of the end M 1 Radial length in the radial direction of the end 1

Claims (6)

タービン動翼の翼根部を翼溝に嵌合して固定するタービン動翼の固定構造であって、
線状部材をコイル状に巻いて形成され、前記翼根部と前記翼溝との間の隙間内に設けられる翼根バネを備え、
前記翼根バネは、外周面が前記翼根部の先端面と前記翼溝の底面とに接触するように、前記隙間の長手方向に沿って配置され、
前記翼根バネの径方向の自然長は、前記翼根部と前記翼溝との間の隙間よりも長いことを特徴とするタービン動翼の固定構造。 A turbine rotor blade fixing structure for fitting and fixing a blade root portion of a turbine rotor blade into a blade groove,
It is formed by winding a linear member in a coil shape, and includes a blade root spring provided in a gap between the blade root portion and the blade groove,
The blade root spring is disposed along the longitudinal direction of the gap so that the outer peripheral surface contacts the tip surface of the blade root portion and the bottom surface of the blade groove,
The turbine blade fixing structure, wherein a natural length in a radial direction of the blade root spring is longer than a gap between the blade root portion and the blade groove. 前記翼根バネの長手方向における中央部と該中央部の両端に位置する両端部とは、前記両端部の径方向の自然長が前記中央部の径方向の自然長よりも小さくなるように構成されていることを特徴とする請求項１に記載のタービン動翼の固定構造。   The central portion in the longitudinal direction of the blade root spring and both end portions located at both ends of the central portion are configured such that the natural length in the radial direction of the both end portions is smaller than the natural length in the radial direction of the central portion. The turbine rotor blade fixing structure according to claim 1, wherein the turbine rotor blade fixing structure is provided. 前記線状部材は、複数の線状体を撚って形成されていることを特徴とする請求項１に記載のタービン動翼の固定構造。   2. The turbine rotor blade fixing structure according to claim 1, wherein the linear member is formed by twisting a plurality of linear bodies. 3. タービン動翼の翼根部と該翼根部が嵌合される翼溝との間に形成された隙間に設けられ、前記翼根部を付勢して前記翼溝に押し付ける翼根バネの脱着方法であって、
前記隙間の長手方向に沿って前記翼根バネに引張荷重を作用させて、前記長手方向と直交する方向の前記翼根バネの長さを縮径させる第１縮径工程と、
前記翼根バネが縮径された状態で、前記タービン動翼を前記翼溝に対して脱着するタービン動翼脱着工程と、
前記タービン動翼が取り外された状態で、前記翼根バネを前記翼溝に対して脱着する第１翼根バネ脱着工程と、
を備えることを特徴とする翼根バネの脱着方法。 A blade root spring detaching method is provided in a gap formed between a blade root portion of a turbine rotor blade and a blade groove in which the blade root portion is fitted, and urges the blade root portion to press it against the blade groove. And
A first diameter reduction step of reducing the length of the blade root spring in a direction perpendicular to the longitudinal direction by applying a tensile load to the blade root spring along the longitudinal direction of the gap;
A turbine rotor blade attaching / detaching step of attaching / detaching the turbine rotor blade to / from the blade groove with the blade root spring having a reduced diameter;
A first blade root spring detaching step of detaching the blade root spring with respect to the blade groove with the turbine rotor blade removed;
A method for attaching and detaching a blade root spring. 前記タービン動翼を前記翼溝に対して脱着した後に、前記縮径された前記翼根バネに作用している前記引張荷重を解放することを特徴とする請求項４に記載の翼根バネの脱着方法。   5. The blade root spring according to claim 4, wherein after the turbine rotor blade is attached to and detached from the blade groove, the tensile load acting on the reduced diameter blade root spring is released. Desorption method. タービン動翼の翼根部と該翼根部が嵌合される翼溝との間に形成された隙間に設けられ、前記翼根部を付勢して前記翼溝に押し付ける翼根バネの脱着方法であって、
前記隙間の長手方向に沿って前記翼根バネに引張荷重を作用させて、前記長手方向と直交する方向の前記翼根バネの長さを縮径させる第２縮径工程と、
前記タービン動翼が前記翼溝に取り付けられた状態で、前記縮径された前記翼根バネを前記隙間に対して脱着する第２翼根バネ脱着工程と、
を備えることを特徴とする翼根バネの脱着方法。 A blade root spring detaching method is provided in a gap formed between a blade root portion of a turbine rotor blade and a blade groove in which the blade root portion is fitted, and urges the blade root portion to press it against the blade groove. And
A second diameter reducing step of reducing the length of the blade root spring in a direction orthogonal to the longitudinal direction by applying a tensile load to the blade root spring along the longitudinal direction of the gap;
A second blade root spring detaching step of detaching the reduced diameter blade root spring with respect to the gap in a state where the turbine rotor blade is attached to the blade groove;
A method for attaching and detaching a blade root spring.
JP2011070812A 2011-03-28 2011-03-28 Turbine blade fixed structure and blade root spring removal method Expired - Fee Related JP5579112B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2011070812A JP5579112B2 (en) 2011-03-28 2011-03-28 Turbine blade fixed structure and blade root spring removal method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2011070812A JP5579112B2 (en) 2011-03-28 2011-03-28 Turbine blade fixed structure and blade root spring removal method

Publications (2)

Publication Number Publication Date
JP2012202391A JP2012202391A (en) 2012-10-22
JP5579112B2 true JP5579112B2 (en) 2014-08-27

Family

ID=47183631

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2011070812A Expired - Fee Related JP5579112B2 (en) 2011-03-28 2011-03-28 Turbine blade fixed structure and blade root spring removal method

Country Status (1)

Country Link
JP (1) JP5579112B2 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9739160B2 (en) * 2013-10-18 2017-08-22 Siemens Aktiengesellschaft Adjustable blade root spring for turbine blade fixation in turbomachinery
WO2015129580A1 (en) * 2014-02-26 2015-09-03 三菱日立パワーシステムズ株式会社 Rotor blade retention device, rotor blade fixing member pressing device, and manufacture method, assembly method and disassembly method of rotating machine
CN114508386A (en) * 2020-11-16 2022-05-17 中国航发商用航空发动机有限责任公司 Blade damper, turbine and aircraft engine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3881844A (en) * 1974-05-28 1975-05-06 Gen Electric Blade platform vibration dampers
US4022545A (en) * 1974-09-11 1977-05-10 Avco Corporation Rooted aerodynamic blade and elastic roll pin damper construction
GB2071775B (en) * 1980-03-14 1983-07-27 Rolls Royce Turbomachine blade vibration damping
JPH01237304A (en) * 1988-03-15 1989-09-21 Toshiba Corp Steam turbine bucket pushing-up device
US6761538B2 (en) * 2002-10-31 2004-07-13 General Electric Company Continual radial loading device for steam turbine reaction type buckets and related method
DE10356237A1 (en) * 2003-12-02 2005-06-30 Alstom Technology Ltd Damping arrangement for a blade of an axial turbine
JP2005273646A (en) * 2004-02-25 2005-10-06 Mitsubishi Heavy Ind Ltd Moving blade element and rotary machine having the moving blade element

Also Published As

Publication number Publication date
JP2012202391A (en) 2012-10-22

Similar Documents

Publication Publication Date Title
KR101531920B1 (en) Radial foil bearing
JP5579112B2 (en) Turbine blade fixed structure and blade root spring removal method
JP5904103B2 (en) Stator manufacturing method, stator, and manufacturing apparatus thereof
JP6124787B2 (en) Lightweight shroud for rotor blades
JP2013525689A5 (en)
EP3084130B1 (en) Method of assembling a set of impellers through tie rods, impeller and turbomachine
US11146153B2 (en) Method of manufacturing a stator of a motor
KR101617901B1 (en) Self-locking nut
US7114927B2 (en) Fixing method for the blading of a fluid-flow machine and fixing arrangement
EP2562357B1 (en) Replaceable staking insert assembly and corresponding method
US10047615B2 (en) Method of mounting rotor blades on a rotor disk, and clamping device for performing such a method
JP5743072B2 (en) Turbine blade fixed structure and turbine blade removal method
JP2011507474A (en) Holding member for commutator rubbing contact portion of electric motor and electric motor
EP2540988B1 (en) Blade outer air seal with a plug assembly and method
JP4834402B2 (en) Crack repair method for rotating electrical machine rotor, crack propagation preventing method for rotating electrical machine rotor, rotating electrical machine rotor, and rotating electrical machine
JP2009165312A (en) Cuff supporter and method of manufacturing stator using the same
JP4834462B2 (en) Method for removing crack in rotating electric machine rotor, method for preventing crack propagation in rotating electric machine rotor, rotating electric machine rotor and rotating electric machine
JP2008002439A (en) Bucket and assembly method
CN103109118A (en) Pre-compressed seal including removable pre-compression member
US20150003979A1 (en) Steam turbine nozzle vane arrangement and method of manufacturing
JP2015002624A (en) Replacement method of stator coil
EP2573327A1 (en) Damping wire, corresponding rotor blade stage, steam turbine and producing method
JP6329471B2 (en) Turbine
JP2012202352A (en) Blade root spring and method of mounting the same
JP4087729B2 (en) Vibration suppression device for gas turbine engine

Legal Events

Date Code Title Description
A621 Written request for application examination

Free format text: JAPANESE INTERMEDIATE CODE: A621

Effective date: 20131101

A977 Report on retrieval

Free format text: JAPANESE INTERMEDIATE CODE: A971007

Effective date: 20140609

TRDD Decision of grant or rejection written
A01 Written decision to grant a patent or to grant a registration (utility model)

Free format text: JAPANESE INTERMEDIATE CODE: A01

Effective date: 20140613

A61 First payment of annual fees (during grant procedure)

Free format text: JAPANESE INTERMEDIATE CODE: A61

Effective date: 20140708

R151 Written notification of patent or utility model registration

Ref document number: 5579112

Country of ref document: JP

Free format text: JAPANESE INTERMEDIATE CODE: R151

S111 Request for change of ownership or part of ownership

Free format text: JAPANESE INTERMEDIATE CODE: R313111

R350 Written notification of registration of transfer

Free format text: JAPANESE INTERMEDIATE CODE: R350

R250 Receipt of annual fees

Free format text: JAPANESE INTERMEDIATE CODE: R250

LAPS Cancellation because of no payment of annual fees