JP2007120460A - Fixing and attaching/detaching method and device of turbine blade - Google Patents

Fixing and attaching/detaching method and device of turbine blade Download PDF

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JP2007120460A
JP2007120460A JP2005316501A JP2005316501A JP2007120460A JP 2007120460 A JP2007120460 A JP 2007120460A JP 2005316501 A JP2005316501 A JP 2005316501A JP 2005316501 A JP2005316501 A JP 2005316501A JP 2007120460 A JP2007120460 A JP 2007120460A
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blade
fixing
turbine
shape memory
memory alloy
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Daijiro Fukuda
大二郎 福田
Kazunari Fujiyama
一成 藤山
Yutaka Ishiwatari
裕 石渡
Takao Inukai
隆夫 犬飼
Norinao Takasu
紀尚 高栖
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Toshiba Corp
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Toshiba Corp
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Abstract

<P>PROBLEM TO BE SOLVED: To provide a fixing and attaching/detaching method of a turbine blade capable of fixing the turbine blade to a turbine rotor during usage of a turbine and capable of easily pulling out the turbine blade upon routine inspection. <P>SOLUTION: When fixing and attaching/detaching the turbine blade 3 by inserting a plurality of the blades 3 in a blade groove 2 from a through portion 4 of the blade groove 2 on the turbine rotor 1 so as to be form-coupled, shape memory alloys 8a and 8b are arranged in a portion where a fixing blade 5 is brought into contact with an adjacent blade 3 or a space between a blade implanted part part 10 of the fixing blade 5 and a bottom part of a fixing glade groove 7. The turbine blade 3 can be fixed and attached/detached by deformation action by temperature variation of the shape memory alloys 8a and 8b. <P>COPYRIGHT: (C)2007,JPO&INPIT

Description

本発明は、タービンロータに施された翼溝の通し部位から翼溝内に複数の翼を挿入して形状結合しタービン翼を固定・着脱するタービン翼の固定・着脱方法および装置に関する。   The present invention relates to a turbine blade fixing / detaching method and apparatus for fixing and removing a turbine blade by inserting a plurality of blades into a blade groove from a passage portion of a blade groove provided on a turbine rotor and coupling the shapes.

一般に、タービンロータへのタービン翼の固定・着脱方法においては、タービン翼をタービンロータに固定する場合には、タービンロータに施された翼溝の通し部位を基準にして、その通し部位から順次タービン翼を挿入して形状結合し、最後に止め翼を通し部位に固定している。一方、タービン翼をタービンロータから着脱する場合には、止め翼の固定を解除した後に、通し部位を基準にタービン翼を抜き出している。このようなタービン翼の固定・着脱方法としては、タービンロータと止め翼とをボルトで固定する方法、止め翼と隣接する箇所にくさびなどを用いて固定する方法、これらの方法を複合したもの等がある。   In general, in the method for fixing / removing a turbine blade to / from the turbine rotor, when the turbine blade is fixed to the turbine rotor, the turbine blades are sequentially inserted from the passage portion with reference to the passage portion of the blade groove formed in the turbine rotor. The wings are inserted and connected in shape, and finally the stop wings are passed through and fixed to the site. On the other hand, when the turbine blades are attached to and detached from the turbine rotor, the turbine blades are extracted with reference to the through portion after the fixing of the stop blades is released. Such turbine blade fixing / detaching methods include a method of fixing the turbine rotor and the retaining blade with bolts, a method of fixing the blade adjacent to the retaining blade using a wedge, a combination of these methods, etc. There is.

タービン翼をタービンロータに固定する方法として、タービンロータの翼溝にある通し位置を介してタービン翼を挿入した後に、通し部位置に充填片を挿入して固定するようにしたものがある（例えば、特許文献１参照）。この充填片は、翼溝輪郭に相当する輪郭により噛み合っている。さらに充填片と翼溝との間隙にくさびを打ち込み、その部分を２つの止めねじによって固定している。
特開２００１−２９５６０３号公報 As a method of fixing the turbine blade to the turbine rotor, there is a method in which after inserting the turbine blade through the passage position in the blade groove of the turbine rotor, the filler piece is inserted and fixed at the passage portion position (for example, , See Patent Document 1). This filling piece is meshed with a contour corresponding to the blade groove contour. Further, a wedge is driven into the gap between the filling piece and the blade groove, and the portion is fixed by two set screws.
JP 2001-295603 A

しかし、従来のタービン翼の固定・着脱方法においては、タービンの定期検査（定検）時のタービン翼の抜き出しにおいて、タービンロータと止め翼との固定を解除しなければならないが、通常、タービンロータと止め翼との固定部分は高温で使用されるためねじが焼き付いていることが多いので、その焼き付いたねじの切断が必要となる。また、タービン翼を取り外して検査をした後に再度タービン翼を取り付ける際にはねじ穴の再加工を行う必要がある。このため、工数が増加したり、再加工が困難であったりする場合がある。   However, in the conventional method for fixing / removing the turbine blade, the turbine rotor and the stationary blade must be unfixed when the turbine blade is extracted during periodic inspection (regular inspection) of the turbine. Since the fixing part between the blade and the retaining blade is used at a high temperature, the screw is often seized, so that the sewn screw must be cut. In addition, when the turbine blade is removed and inspected, and the turbine blade is attached again, it is necessary to rework the screw holes. For this reason, man-hours may increase or reworking may be difficult.

本発明の目的は、タービンの使用時はタービン翼をタービンロータに固定し、定検時は容易にタービンの翼の抜き出しを行うことができるタービン翼の固定・着脱方法および装置を得ることである。   An object of the present invention is to obtain a turbine blade fixing / detaching method and apparatus capable of fixing a turbine blade to a turbine rotor during use of a turbine and easily extracting a turbine blade during regular inspection. .

本発明のタービン翼の固定・着脱方法は、タービンロータに施された翼溝の通し部位から前記翼溝内に複数の翼を挿入して形状結合しタービン翼を固定・着脱するタービン翼の固定・着脱方法において、止め翼の隣接翼と接触する箇所もしくは止め翼の翼植込み部と翼溝の底部との間に形状記憶合金を配置し、形状記憶合金の温度変化による変形作用によりタービン翼を固定・着脱することを特徴とする。   The turbine blade fixing / detaching method of the present invention is a turbine blade fixing method in which a plurality of blades are inserted into the blade grooves from the blade groove through-holes formed in the turbine rotor, and the turbine blades are fixed / removed.・ In the attachment / detachment method, a shape memory alloy is placed between the contact point with the adjacent blade of the stationary blade or between the blade implanted portion of the stationary blade and the bottom of the blade groove, and the turbine blade is moved by the deformation action due to the temperature change of the shape memory alloy. It is characterized by being fixed and detachable.

本発明によれば、形状記憶合金の温度変化による変形作用によりタービン翼を固定・着脱するので、タービンの使用時はタービン翼をタービンロータに固定し、定検時は容易にタービンの翼の抜き出しを行うことができる。従って、工数低減や再加工が必要なくなることによるコストダウンを図ることができる。   According to the present invention, the turbine blades are fixed and detached by the deformation action due to the temperature change of the shape memory alloy. Therefore, the turbine blades are fixed to the turbine rotor when the turbine is used, and the turbine blades are easily extracted during the regular inspection. It can be performed. Therefore, it is possible to reduce costs by reducing man-hours and eliminating the need for reworking.

（第１の実施の形態）
図１は本発明の第１の実施の形態に係わるタービン翼の固定・着脱方法を実現するためのタービンロータおよびタービン翼の部分斜視図である。タービンロータ１に翼植込み形状を有する翼溝２が設けられ、翼溝２の少なくとも１つの位置において、その翼溝２に沿って通し部位４が設けられている。この通し部位４を介して翼３が翼溝２内に挿入され翼３が形状結合する。翼３の挿入後に止め翼５が通し部位４に挿入される。 (First embodiment)
FIG. 1 is a partial perspective view of a turbine rotor and a turbine blade for realizing the turbine blade fixing / detaching method according to the first embodiment of the present invention. A blade groove 2 having a blade implantation shape is provided in the turbine rotor 1, and a passage portion 4 is provided along the blade groove 2 at at least one position of the blade groove 2. The blade 3 is inserted into the blade groove 2 through the passage portion 4, and the blade 3 is shape-coupled. After insertion of the wing 3, the stop wing 5 is inserted into the through portion 4.

そして、止め翼５の隣接翼接触部６や止め翼溝７の底部に形状記憶合金８ａ、８ｂを配置する。形状記憶合金８ａ、８ｂは温度が変化することで変形して、止め翼５をタービンロータ１に固定したり離脱したりする。   Then, the shape memory alloys 8 a and 8 b are arranged on the adjacent blade contact portion 6 of the stop blade 5 and the bottom of the stop blade groove 7. The shape memory alloys 8 a and 8 b are deformed by changing the temperature, and the retaining blade 5 is fixed to or detached from the turbine rotor 1.

図２は本発明の第１の実施の形態においてタービンロータ１への翼３の着脱の説明図である。図２に示すように、まず、翼３の挿入後に予め液体窒素でおよそ−１０℃に冷却した形状記憶合金板８ｂを止め翼溝７の底部に設置し、止め翼５を通し部位４に挿入した後、形状記憶合金板８ｂに温風を当てて約１０℃程度に加熱する。そうすると、形状記憶合金板８ｂは曲げ方向に変形し、止め翼５の植込み部１０を押さえ付ける。一方、翼３の抜き取りは、形状記憶合金板８ｂに冷風を当てて約−１０℃程度に冷却する。冷却により形状記憶合金板８ｂは真っ直ぐに変形して、止め翼５の植込み部１０への押さえ付けを解除する。   FIG. 2 is an explanatory view of the attachment / detachment of the blade 3 to / from the turbine rotor 1 in the first embodiment of the present invention. As shown in FIG. 2, first, after inserting the blade 3, the shape memory alloy plate 8 b that has been cooled to about −10 ° C. with liquid nitrogen in advance is placed at the bottom of the retaining blade groove 7, and the retaining blade 5 is inserted into the site 4. After that, the shape memory alloy plate 8b is heated to about 10 ° C. by applying warm air. Then, the shape memory alloy plate 8b is deformed in the bending direction and presses the implanted portion 10 of the retaining blade 5. On the other hand, the blade 3 is extracted by applying cold air to the shape memory alloy plate 8b and cooling to about -10 ° C. The shape memory alloy plate 8b is straightly deformed by cooling, and the pressing of the retaining blade 5 to the implanted portion 10 is released.

以上の説明では、止め翼溝７の底部に１つの板の形状記憶合金８ｂを用いた場合について説明したが、曲げ変形により止め翼５の植込み部１０を押さえ付けることができれば、板でなく条や棒などでもよく、また複数の形状記憶合金８ｂを用いてもよい。   In the above description, the case where the shape memory alloy 8b of one plate is used at the bottom of the retaining blade groove 7 has been described. However, if the implanted portion 10 of the retaining blade 5 can be pressed by bending deformation, not the plate but the strip. A plurality of shape memory alloys 8b may be used.

第１の実施の形態によれば、止め翼５の翼植込み部１０と翼溝７の底部との間に配置された形状記憶合金８ｂにより、高温時に曲げ方向に変形して翼植込み部１０を押さえ、低温時に真っ直ぐに変形して翼植込み部１０の押さえを解除するので、クサビなどの当て板やボルトを使用せずに止め翼５をタービンロータ１に固定できる。従って、定検時における翼３の抜き出しが容易にできるので工数低減によるコストダウンが可能である。   According to the first embodiment, the shape memory alloy 8b disposed between the blade implantation portion 10 of the stationary blade 5 and the bottom portion of the blade groove 7 deforms the blade implantation portion 10 by deforming in the bending direction at a high temperature. The retainer blade 5 can be fixed to the turbine rotor 1 without using a stopper plate such as a wedge or a bolt because the retainer is deformed straightly at a low temperature to release the retainer of the blade implantation portion 10. Accordingly, the blade 3 can be easily extracted during the regular inspection, so that the cost can be reduced by reducing the number of man-hours.

（第２の実施の形態）
図３は本発明の第２の実施の形態に係わるタービン翼の固定・着脱方法を実現するためのタービンロータ１への翼３の着脱の説明図である。この第２の実施の形態は、第１の実施の形態に対し、高温時に曲げ方向に変形して翼植込み部１０を押さえ、低温時に真っ直ぐに変形して翼植込み部１０の押さえを解除する形状記憶合金に代えて、高温時に伸びて翼植込み部１０を押さえ、低温時に縮んで植込み部１０の押さえを解除する形状記憶合金８ｂを用いたものである。 (Second Embodiment)
FIG. 3 is an explanatory view of attachment / detachment of the blade 3 to / from the turbine rotor 1 for realizing the turbine blade fixing / detaching method according to the second embodiment of the present invention. In contrast to the first embodiment, the second embodiment deforms in the bending direction at a high temperature to press the wing implantation part 10, and deforms straight at a low temperature to release the wing implantation part 10. Instead of the memory alloy, a shape memory alloy 8b is used which extends at a high temperature and presses the wing implantation part 10 and contracts at a low temperature to release the holding of the implantation part 10.

図３において、翼３の挿入後に液体窒素で約−１０℃程度に冷却した２つの形状記憶合金８ｂをスプリング状に縮んだ状態に変形させて止め翼溝７の底部に設置する。そして、止め翼５を通し部位４に挿入した後に、形状記憶合金８ｂに温風を当てて約１０℃程度に加熱する。そうすると、形状記憶合金８ｂは伸びて止め翼５の植込み部１０を押さえ付ける。一方、翼３の抜き取りは、形状記憶合金８ｂに冷風を当てて約−１０℃程度に冷却する。冷却により形状記憶合金８ｂは縮んで止め翼５の植込み部１０への押さえ付けを解除する。   In FIG. 3, two shape memory alloys 8 b cooled to about −10 ° C. with liquid nitrogen after the blade 3 is inserted are deformed into a spring-like state and placed at the bottom of the stop blade groove 7. Then, after inserting the retaining blade 5 into the part 4, the shape memory alloy 8b is heated to about 10 ° C. by applying hot air. Then, the shape memory alloy 8b extends and presses the implanted portion 10 of the stop wing 5. On the other hand, the blade 3 is extracted by cooling the shape memory alloy 8b with cold air to about -10 ° C. By cooling, the shape memory alloy 8b contracts to release the retaining blade 5 from being pressed against the implanted portion 10.

以上の説明では、止め翼溝７の底部に備えられた形状記憶合金８ｂの形状をスプリング状としたが、伸び縮みにより止め翼５の植込み部１０を押さえ付けることができればいずれの形状でもよく、また２つ以上の形状記憶合金８ｂを用いてもよい。   In the above description, the shape of the shape memory alloy 8b provided at the bottom of the stop blade groove 7 is a spring shape, but any shape may be used as long as the implanted portion 10 of the stop blade 5 can be pressed by expansion and contraction. Two or more shape memory alloys 8b may be used.

第２の実施の形態によれば、止め翼５の翼植込み部１０と翼溝７の底部との間に配置されたスプリング状の形状記憶合金８ｂにより、高温時に伸びて翼植込み部１０を押さえ、低温時に縮んで翼植込み部１０の押さえを解除するので、翼３の抜き出しが容易にできる。従って、定検時等での翼３の着脱の工数を低減できコストダウンを図れる。   According to the second embodiment, the spring-shaped shape memory alloy 8b disposed between the blade implantation portion 10 of the stationary blade 5 and the bottom portion of the blade groove 7 extends and holds the blade implantation portion 10 at a high temperature. The blade 3 is shrunk at a low temperature and the pressing of the blade implantation part 10 is released, so that the blade 3 can be easily extracted. Therefore, it is possible to reduce the man-hours for attaching and detaching the blade 3 at the time of regular inspection or the like and to reduce the cost.

（第３の実施の形態）
図４は本発明の第３の実施の形態に係わるタービン翼の固定・着脱方法を実現するための止め翼５の隣接翼３ａ、３ｂと接触する箇所に配置された形状記憶合金８ａの説明図である。この第３の実施の形態は、第１の実施の形態に対し、予め形状記憶合金８ａを係止するための隣接翼接触部溝１１を設けたものである。 (Third embodiment)
FIG. 4 is an explanatory view of a shape memory alloy 8a arranged at a location where the stationary blade 5 contacts with the adjacent blades 3a and 3b for realizing the turbine blade fixing / removing method according to the third embodiment of the present invention. It is. In the third embodiment, adjacent blade contact portion grooves 11 for locking the shape memory alloy 8a are provided in advance with respect to the first embodiment.

図４において、止め翼５がその隣接翼３ａ、３ｂと接触する箇所（隣接翼接触部６）に、予め形状記憶合金８ａを係止するための隣接翼接触部溝１１が設けられ、その隣接翼接触部溝１１には形状記憶合金８ａが配置されている。   In FIG. 4, the adjacent blade contact part groove | channel 11 for latching the shape memory alloy 8a previously is provided in the location (adjacent blade contact part 6) where the stop blade 5 contacts the adjacent blades 3a and 3b. A shape memory alloy 8 a is disposed in the blade contact portion groove 11.

まず、タービンロータ１の翼溝２に翼３を挿入し、その挿入後に予め液体窒素で約−１０℃程度に冷却して形状を真っ直ぐにしておいた左右２つの形状記憶合金８ａを止め翼５の隣接翼接触部溝１１に設置する。そして、止め翼５を通し部位４に挿入した後に、形状記憶合金８ａに温風を当てて約１０℃程度に加熱する。形状記憶合金８ａは曲げ方向に変形し、形状記憶合金８ａの両端部分が止め翼５の隣接翼接触部溝１１に接触し、中央部分が隣接翼３ａ、３ｂに接触して止め翼５と隣接翼３ａ、３ｂを周方向に押さえつけて固定する。   First, the blade 3 is inserted into the blade groove 2 of the turbine rotor 1, and after the insertion, the two left and right shape memory alloys 8a that have been cooled to about -10 [deg.] C. in advance with liquid nitrogen and straightened are fixed to the blade 5 Is installed in the adjacent blade contact portion groove 11. And after inserting the stop blade 5 in the site | part 4, a hot air is applied to the shape memory alloy 8a, and it heats to about 10 degreeC. The shape memory alloy 8a is deformed in the bending direction, both end portions of the shape memory alloy 8a are in contact with the adjacent blade contact portion groove 11 of the stop blade 5, and the central portion is in contact with the adjacent blades 3a and 3b and adjacent to the stop blade 5. The wings 3a and 3b are pressed and fixed in the circumferential direction.

図５は本発明の第３の実施の形態に係わるタービン翼の固定・着脱方法を実現するための止め翼５の隣接翼３ａ、３ｂと接触する箇所に配置された形状記憶合金８ａの他の一例の説明図である。板の形状記憶合金８ａが止め翼５および隣接翼３ａ、３ｂに接触しており、周方向への押さえ付けによって止め翼５と隣接翼３ａ、３ｂとが固定されている状態であれば、形状記憶合金８ａは、図５のように両端部分と中央部分の接触箇所が逆でもよい。   FIG. 5 shows another shape memory alloy 8a disposed at a position where the blade 5 is in contact with the adjacent blades 3a, 3b for realizing the turbine blade fixing / detaching method according to the third embodiment of the present invention. It is explanatory drawing of an example. If the shape memory alloy 8a of the plate is in contact with the stop blade 5 and the adjacent blades 3a and 3b, and the stop blade 5 and the adjacent blades 3a and 3b are fixed by pressing in the circumferential direction, the shape As shown in FIG. 5, the memory alloy 8a may have opposite contact portions between the both end portions and the central portion.

次に、翼３の抜き取りは、形状記憶合金８ａに冷風を当てて約−１０℃程度に冷却する。冷却により形状記憶合金８ａは真っ直ぐに変形して止め翼５と隣接翼３ａ、３ｂとの接触を解除する。   Next, the blade 3 is extracted by cooling the shape memory alloy 8a with cold air to about -10 ° C. By cooling, the shape memory alloy 8a is straightly deformed to release the contact between the stop blade 5 and the adjacent blades 3a and 3b.

以上の説明では、止め翼５に隣接翼接触部溝１１を設けた場合について説明したが、隣接翼３ａ、３ｂにも隣接翼接触部溝１２を設けるようにしてもよい。図６は隣接翼３ａ、３ｂにも隣接翼接触部溝１２を設けた場合の形状記憶合金８ａの説明図である。翼３の挿入後に予め液体窒素で約−１０℃程度に冷却して形状を真っ直ぐにしておいた左右２つの形状記憶合金８ａを止め翼５の隣接翼接触部溝１１に設置する。   In the above description, the case where the adjacent blade contact portion groove 11 is provided in the stop blade 5 has been described, but the adjacent blade contact portion groove 12 may also be provided in the adjacent blade 3a, 3b. FIG. 6 is an explanatory view of the shape memory alloy 8a in the case where the adjacent blade contact portion groove 12 is provided also in the adjacent blades 3a and 3b. After the blade 3 is inserted, the two left and right shape memory alloys 8 a that have been cooled to about −10 ° C. with liquid nitrogen and straightened are placed in the adjacent blade contact portion groove 11 of the stop blade 5.

そして、止め翼５を通し部位４に挿入した後、形状記憶合金８ａに温風を当てて約１０℃程度に加熱する。形状記憶合金８ａは曲げ方向に変形し、形状記憶合金８ａの両端部分が止め翼５の隣接翼接触部溝１１に接触し、中央部分が隣接翼３ａ、３ｂの隣接翼接触部溝１２に接触して止め翼５と隣接翼３ａ、３ｂとを周方向に押さえ付け、かつ、双方の翼３ａ、３ｂの隣接翼接触部溝１２に引っ掛けて固定する。   And after inserting the stop blade 5 in the site | part 4, a hot air is applied to the shape memory alloy 8a, and it heats to about 10 degreeC. The shape memory alloy 8a is deformed in the bending direction, both end portions of the shape memory alloy 8a are in contact with the adjacent blade contact portion groove 11 of the stop blade 5, and the central portion is in contact with the adjacent blade contact portion groove 12 of the adjacent blade 3a, 3b. Then, the retaining blade 5 and the adjacent blades 3a and 3b are pressed in the circumferential direction, and are hooked and fixed to the adjacent blade contact portion grooves 12 of both blades 3a and 3b.

形状記憶合金８ａが止め翼５および隣接翼３ａ、３ｂに接触しており、周方向への押さえ付けおよび隣接翼接触部溝１１との引っ掛けによって、止め翼５と隣接翼３ａ、３ｂが固定されている状態であれば、形状記憶合金８ａは、図７のように両端部分と中央部分の接触箇所が逆でもよい。翼３ａ、３ｂの抜き取りは、形状記憶合金８ａに冷風を当てて約−１０℃程度に冷却する。形状記憶合金８ａは真っ直ぐに変形して止め翼５と隣接翼３ａ、３ｂとの接触および引っ掛けを解除する。   The shape memory alloy 8a is in contact with the stop blade 5 and the adjacent blades 3a, 3b, and the stop blade 5 and the adjacent blades 3a, 3b are fixed by pressing in the circumferential direction and hooking with the adjacent blade contact portion groove 11. As long as the shape memory alloy 8a is in such a state, the contact portions of both end portions and the central portion may be reversed as shown in FIG. The blades 3a and 3b are extracted by applying cold air to the shape memory alloy 8a and cooling to about -10 ° C. The shape memory alloy 8a is deformed straight to release the contact and hooking between the stop blade 5 and the adjacent blades 3a and 3b.

以上の説明では、止め翼５の隣接翼接触部溝１１に板の形状記憶合金８ａを用いたが、止め翼５と隣接翼３ａ、３ｂとを周方向に押さえ付けることができれば、条や棒の形状記憶合金８ａなどでもよく、左右２つの形状記憶合金８ａを多段に取り付けるようにしてもよい。   In the above description, the shape memory alloy 8a of the plate is used for the adjacent blade contact portion groove 11 of the stop blade 5. However, if the stop blade 5 and the adjacent blades 3a and 3b can be pressed in the circumferential direction, a strip or a rod can be used. The shape memory alloy 8a may be used, and the left and right shape memory alloys 8a may be attached in multiple stages.

第３の実施の形態によれば、隣接翼接触部溝１１、１５を設け形状記憶合金８ａにより止め翼５と隣接翼３ａ、３ｂを周方向に押さえ付け、かつ、引っ掛けることができるので、止め翼５と隣接翼３ａ、３ｂとの係止力が向上する。   According to the third embodiment, the adjacent blade contact portion grooves 11 and 15 are provided, and the stop blade 5 and the adjacent blades 3a and 3b can be pressed and hooked in the circumferential direction by the shape memory alloy 8a. The locking force between the blade 5 and the adjacent blades 3a and 3b is improved.

（第４の実施の形態）
図８は、本発明の第４の実施の形態に係わるタービン翼の固定・着脱方法の形状記憶合金の温度変化に対する説明図である。この第４の実施の形態は、第１の実施の形態乃至第３の実施の形態のいずれかに対し、隣接翼接触部６もしくは止め翼溝７の底部のいずれかに備えられた形状記憶合金８ａ、８ｂが変形する温度は、タービン停止時温度Ｔ１よりも低い温度であり、形状記憶合金８ａ、８ｂの変形による固定完了温度Ｔ２は形状記憶合金８ａ、８ｂの変形による着脱可能温度Ｔ３より高い温度としたものである。 (Fourth embodiment)
FIG. 8 is an explanatory view with respect to the temperature change of the shape memory alloy in the method for fixing and detaching a turbine blade according to the fourth embodiment of the present invention. In the fourth embodiment, the shape memory alloy provided in either the adjacent blade contact portion 6 or the bottom portion of the stop blade groove 7 with respect to any of the first to third embodiments. The temperature at which 8a and 8b are deformed is lower than the turbine stop temperature T1, and the fixing completion temperature T2 due to the deformation of the shape memory alloys 8a and 8b is higher than the detachable temperature T3 due to the deformation of the shape memory alloys 8a and 8b. Temperature.

この第４の実施の形態ではタービン停止時温度Ｔ１を約２５℃程度とし、それよりも低い温度として固定完了温度Ｔ２を約１０℃程度、着脱可能温度Ｔ３を約−１０℃程度と設定したが、タービンを設置する環境によって固定完了温度Ｔ２もしくは着脱可能温度Ｔ３を変更した形状記憶合金８ａ、８ｂを用いてもよい。例えば、年間の最低気温が０℃であり、かつ、タービン停止時の温度が外気温度と同等である環境の場合、０℃でも翼が固定するために固定完了温度Ｔ２を約−１０℃程度、着脱可能温度Ｔ３を約−２０℃程度とする機能を備えた形状記憶合金を用いる。   In the fourth embodiment, the turbine stop temperature T1 is set to about 25 ° C., and the fixing completion temperature T2 is set to about 10 ° C. and the detachable temperature T3 is set to about −10 ° C. as lower temperatures. The shape memory alloys 8a and 8b in which the fixing completion temperature T2 or the detachable temperature T3 is changed depending on the environment in which the turbine is installed may be used. For example, in an environment where the annual minimum temperature is 0 ° C. and the temperature when the turbine is stopped is equal to the outside air temperature, the fixing completion temperature T2 is about −10 ° C. in order to fix the blades even at 0 ° C. A shape memory alloy having a function of setting the detachable temperature T3 to about −20 ° C. is used.

第４の実施の形態によれば、形状記憶合金は高温時には翼植込み部を押さえ、低温時には植込み部の押さえの解除を確実にできる。   According to the fourth embodiment, the shape memory alloy can press the wing implantation part at high temperature, and can reliably release the holding of the implantation part at low temperature.

以上の各実施の形態では、形状記憶合金８ａ、８ｂを加熱する媒体として温風（空気）、冷却する媒体として冷風（空気）または液体窒素を使用したが、形状記憶合金８ａ、８ｂを任意の形状にすることができれば、冷却媒体は、水、ペルチェ素子、加熱媒体は水、油、ヒータ、ペルチェ素子などでもよい。また、加熱冷却方法は形状記憶合金８ａ、８ｂを直接的に加熱冷却したが、形状記憶合金８ａ、８ｂを任意の形状にすることができれば、周囲の部品を加熱冷却して熱伝導を利用した間接的方法でもよい。また、止め翼５や隣接翼３ａ、３ｂの翼植込み形状、タービンロータ１に備えられた止め翼溝７、翼溝２、通し部位４の形状は、形状記憶合金８ａ、８ｂによる固定・着脱を可能するものであればいずれの形状でもよい。   In each of the above embodiments, hot air (air) is used as a medium for heating the shape memory alloys 8a and 8b, and cold air (air) or liquid nitrogen is used as a medium for cooling. However, the shape memory alloys 8a and 8b can be arbitrarily set. The cooling medium may be water, a Peltier element, and the heating medium may be water, oil, a heater, a Peltier element, or the like as long as it can be shaped. In addition, although the shape memory alloys 8a and 8b are directly heated and cooled in the heating and cooling method, if the shape memory alloys 8a and 8b can be formed into an arbitrary shape, the surrounding components are heated and cooled to use heat conduction. An indirect method may be used. In addition, the shape of the stationary blade 5 and the adjacent blades 3a and 3b, and the shape of the stationary blade groove 7, the blade groove 2, and the threaded portion 4 provided in the turbine rotor 1 are fixed and attached by shape memory alloys 8a and 8b. Any shape is possible if possible.

本発明の第１の実施の形態に係わるタービン翼の固定・着脱方法を実現するためのタービンロータおよびタービン翼の部分斜視図。1 is a partial perspective view of a turbine rotor and a turbine blade for realizing the turbine blade fixing / detaching method according to the first embodiment of the present invention. 本発明の第１の実施の形態においてタービンロータへの翼の着脱の説明図。Explanatory drawing of the attachment or detachment of the blade | wing to the turbine rotor in the 1st Embodiment of this invention. 本発明の第２の実施の形態に係わるタービン翼の固定・着脱方法を実現するためのタービンロータへの翼の着脱の説明図。Explanatory drawing of attachment / detachment of the blade to the turbine rotor for implement | achieving the fixing / detachment method of the turbine blade concerning the 2nd Embodiment of this invention. 本発明の第３の実施の形態に係わるタービン翼の固定・着脱方法を実現するための止め翼の隣接翼と接触する箇所に配置された形状記憶合金の説明図。Explanatory drawing of the shape memory alloy arrange | positioned in the location which contacts the adjacent blade of the stop blade for implement | achieving the fixing / detaching method of the turbine blade concerning the 3rd Embodiment of this invention. 本発明の第３の実施の形態に係わるタービン翼の固定・着脱方法を実現するための止め翼の隣接翼と接触する箇所に配置された形状記憶合金の他の一例の説明図。Explanatory drawing of another example of the shape memory alloy arrange | positioned in the location which contacts the adjacent blade of the stop blade for implement | achieving the fixing / detaching method of the turbine blade concerning the 3rd Embodiment of this invention. 本発明の第３の実施の形態に係わるタービン翼の固定・着脱方法を実現するために隣接翼にも隣接翼接触部溝を設けた場合の形状記憶合金の説明図。Explanatory drawing of the shape memory alloy at the time of providing an adjacent blade contact part groove | channel also in an adjacent blade in order to implement | achieve the fixing / detaching method of the turbine blade concerning the 3rd Embodiment of this invention. 本発明の第３の実施の形態に係わるタービン翼の固定・着脱方法を実現するために隣接翼にも隣接翼接触部溝を設けた場合の形状記憶合金の他の一例の説明図。Explanatory drawing of another example of the shape memory alloy at the time of providing an adjacent blade contact part groove | channel also in an adjacent blade in order to implement | achieve the fixing / detachment method of the turbine blade concerning the 3rd Embodiment of this invention. 本発明の第４の実施の形態に係わるタービン翼の固定・着脱方法の形状記憶合金の温度変化に対する説明図。Explanatory drawing with respect to the temperature change of the shape memory alloy of the fixing / detaching method of the turbine blade concerning the 4th Embodiment of this invention.

符号の説明Explanation of symbols

１…タービンロータ、２…翼溝、３…翼、４…通し部位、５…止め翼、６…隣接翼接触部、７…止め翼溝、８…形状記憶合金、１０…翼植込み部、１１…隣接翼接触部溝、１２…隣接翼接触部溝 DESCRIPTION OF SYMBOLS 1 ... Turbine rotor, 2 ... Blade groove, 3 ... Blade, 4 ... Passing part, 5 ... Stop blade, 6 ... Adjacent blade contact part, 7 ... Stop blade groove, 8 ... Shape memory alloy, 10 ... Blade implantation part, 11 ... adjacent blade contact part groove, 12 ... adjacent blade contact part groove

Claims (11)

タービンロータに施された翼溝の通し部位から前記翼溝内に複数の翼を挿入して形状結合しタービン翼を固定・着脱するタービン翼の固定・着脱方法において、止め翼の隣接翼と接触する箇所もしくは止め翼の翼植込み部と翼溝の底部との間に形状記憶合金を配置し、形状記憶合金の温度変化による変形作用によりタービン翼を固定・着脱することを特徴とするタービン翼の固定・着脱方法。 In a turbine blade fixing / detaching method in which a plurality of blades are inserted into the blade groove from the blade groove passage portion provided in the turbine rotor to form a shape and the turbine blade is fixed / removed, contact with the adjacent blade of the stop blade A shape memory alloy is disposed between the blade portion to be fixed or the blade embedded portion of the retaining blade and the bottom of the blade groove, and the turbine blade is fixed and attached by a deformation action due to a temperature change of the shape memory alloy. Fixing / detaching method. 止め翼の翼植込み部と翼溝の底部との間に配置された形状記憶合金は、高温時に曲げ方向に変形して翼植込み部を押さえ、低温時に真っ直ぐに変形して翼植込み部の押さえを解除することを特徴とする請求項１記載のタービン翼の固定・着脱方法。 The shape memory alloy placed between the blade implantation part of the stop blade and the bottom of the blade groove deforms in the bending direction at high temperatures to hold down the blade implantation part, and deforms straight at low temperatures to hold down the blade implantation part. The turbine blade fixing / detaching method according to claim 1, wherein the turbine blade fixing / detaching method is performed. 止め翼の翼植込み部と翼溝の底部との間に配置された形状記憶合金は、高温時に伸びて翼植込み部を押さえ、低温時に縮んで植込み部の押さえを解除することを特徴とする請求項１記載のタービン翼の固定・着脱方法。 The shape memory alloy disposed between the blade implantation portion of the stop blade and the bottom portion of the blade groove extends at a high temperature to hold down the blade implantation portion, and contracts at a low temperature to release the holding of the implantation portion. Item 5. A method of fixing and removing a turbine blade according to Item 1. 止め翼の隣接翼と接触する箇所に配置された形状記憶合金は、高温時に曲げ方向に変形してその中央部分または両端部分が止め翼と隣接翼とに接触して固定し、低温時に真っ直ぐに変形して止め翼と隣接翼との接触固定を解除することを特徴とする請求項１記載のタービン翼の固定・着脱方法。 The shape memory alloy placed in contact with the adjacent blade of the stop blade deforms in the bending direction at high temperatures, and its central part or both ends touch and fix the stop blade and adjacent blades, and straightens at low temperatures. The method for fixing / removing a turbine blade according to claim 1, wherein the fixing of the contact between the stop blade and the adjacent blade is released by deformation. 止め翼の隣接翼と接触する箇所に配置する形状記憶合金を係止するための隣接翼接触部溝を前記止め翼および隣接翼の少なくともいずれか一方に予め設けておき、前記形状記憶合金は、高温時に曲げ方向に変形してその中央部分または両端部分がそれぞれ前記隣接翼接触部溝に接触し引っ掛けて固定し、低温時に真っ直ぐに変形して前記隣接翼接触部溝との接触や引っ掛けを解除することを特徴とする請求項１記載のタービン翼の固定・着脱方法。 An adjacent blade contact portion groove for locking a shape memory alloy disposed at a location where the stop blade comes into contact with an adjacent blade is provided in advance in at least one of the stop blade and the adjacent blade, and the shape memory alloy is At high temperature, it deforms in the bending direction, and its central part or both end parts contact and fix the adjacent blade contact part groove, respectively, and deforms straightly at low temperature to release contact and hook with the adjacent blade contact part groove. The method for fixing / removing a turbine blade according to claim 1, wherein: 前記形状記憶合金が変形して前記タービン翼を固定する構造となる温度は、タービン停止時の温度以下の温度であり、前記形状記憶合金が変形して着脱可能な構造となる温度より高い温度であることを特徴とする請求項１記載のタービン翼の固定・着脱方法。 The temperature at which the shape memory alloy is deformed to fix the turbine blade is a temperature that is equal to or lower than the temperature when the turbine is stopped, and is higher than the temperature at which the shape memory alloy is deformed to be removable. The turbine blade fixing / detaching method according to claim 1, wherein the turbine blade fixing / removing method is provided. 前記形状記憶合金が変形して前記タービン翼を着脱可能な構造となる温度は、タービン停止時の温度以下の温度であり、前記形状記憶合金が変形して固定する構造となる温度より低い温度であることを特徴とする請求項１記載のタービン翼の固定・着脱方法。 The temperature at which the shape memory alloy is deformed so that the turbine blade can be attached and detached is a temperature lower than the temperature when the turbine is stopped, and the temperature is lower than the temperature at which the shape memory alloy is deformed and fixed. The turbine blade fixing / detaching method according to claim 1, wherein the turbine blade fixing / removing method is provided. 前記形状記憶合金の温度変化は、媒体により直接的もしくは間接的に加熱冷却を行い、前記形状記憶合金が変形して前記タービン翼を固定および着脱することを特徴とする請求項１記載のタービン翼の固定・着脱方法。 2. The turbine blade according to claim 1, wherein the temperature change of the shape memory alloy is directly or indirectly heated and cooled by a medium, and the shape memory alloy is deformed to fix and remove the turbine blade. Fixing / detaching method. 直接的もしくは間接的に加熱を行うための媒体は、空気、水、油、ヒータ、ペルチェ素子であることを特徴とする請求項８記載のタービン翼の固定・着脱方法。 9. The turbine blade fixing / detaching method according to claim 8, wherein the medium for directly or indirectly heating is air, water, oil, a heater, or a Peltier element. 直接的もしくは間接的に冷却を行うための媒体は、空気、水、液体窒素、ペルチェ素子であることを特徴とする請求項８記載のタービン翼の固定・着脱方法。 The turbine blade fixing / detaching method according to claim 8, wherein the medium for directly or indirectly cooling is air, water, liquid nitrogen, or a Peltier element. タービンロータに施された翼溝の通し部位から前記翼溝内に複数の翼を挿入して形状結合しタービン翼を固定・着脱するタービン翼の固定・着脱装置において、止め翼の隣接翼と接触する箇所もしくは止め翼の翼植込み部と翼溝の底部との間に配置される形状記憶合金を設け、前記形状記憶合金の温度変化による変形作用によりタービン翼を固定・着脱することを特徴とするタービン翼の固定・着脱装置。
In a turbine blade fixing / removing device for fixing / removing a turbine blade by inserting a plurality of blades into the blade groove from the blade groove passage portion provided in the turbine rotor and fixing the turbine blade, contact with the adjacent blade of the stop blade A shape memory alloy disposed between the blade implantation portion of the retaining blade or the blade groove and the bottom of the blade groove, and the turbine blade is fixed and attached by a deformation action due to a temperature change of the shape memory alloy. Turbine blade fixing / detaching device.
JP2005316501A 2005-10-31 2005-10-31 Fixing and attaching/detaching method and device of turbine blade Pending JP2007120460A (en)

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US9689271B2 (en) 2011-05-17 2017-06-27 Snecma Turbine engine impeller
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CN103717840B (en) * 2011-08-03 2015-12-23 斯奈克玛 Bladed rotor for turbine engine is taken turns
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CN106170608A (en) * 2014-01-21 2016-11-30 通用电器技术有限公司 For rotating or the mechanical fastening system of static component
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JP2019056326A (en) * 2017-09-21 2019-04-11 三菱日立パワーシステムズ株式会社 Turbine blade group and rotary machine comprising the same

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