JP5316042B2 - Steam turbine rotor - Google Patents

Steam turbine rotor Download PDF

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JP5316042B2
JP5316042B2 JP2009026275A JP2009026275A JP5316042B2 JP 5316042 B2 JP5316042 B2 JP 5316042B2 JP 2009026275 A JP2009026275 A JP 2009026275A JP 2009026275 A JP2009026275 A JP 2009026275A JP 5316042 B2 JP5316042 B2 JP 5316042B2
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rotor
blade
coating
rotor disk
steam
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JP2010180819A (en
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忠弘 岩倉
吉弘 酒井
憲司 中村
秀雄 加藤
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Fuji Electric Co Ltd
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Description

この発明は、地熱蒸気タービンに適用する蒸気タービンのロータに関し、詳しくはロータディスクの外周縁に沿ってアキシャルエントリー式に固定した動翼の脚部とロータディスクの翼溝との嵌合部に発生する隙間腐食，腐食疲労，応力腐食割れを防ぐ防食構造に係わる。   The present invention relates to a rotor of a steam turbine applied to a geothermal steam turbine, and more specifically, occurs at a fitting portion between a rotor blade leg fixed in an axial entry manner along an outer peripheral edge of the rotor disk and a blade groove of the rotor disk. It relates to a corrosion prevention structure that prevents crevice corrosion, corrosion fatigue, and stress corrosion cracking.

頭記の地熱蒸気タービンでは、周知のように各段のロータディスクの周縁に沿って動翼の翼列が装着されており、特に低圧段落の動翼は高い強度が要求されることからアキシャルエントリー式の固定構造が一般に採用されている。   In the geothermal steam turbine mentioned above, blade rows of rotor blades are installed along the periphery of each stage of the rotor disk as is well known. A fixed structure of the formula is generally adopted.

ここで、アキシャルエントリー式による動翼の基本的な固定構造を図４，図５に示す。各図において、１はロータディスク、２は動翼であり、図５で示すように、動翼２には翼幹２ａの根元にクリスマスツリー形状の脚部２ｂが形成されている。一方、ロータディスク１には、その外周縁に沿って前記脚部２ｂの形状に対応したクリスマスツリー形状の翼溝１ａが軸方向に刻設されている。   Here, the basic fixing structure of the moving blade by the axial entry type is shown in FIGS. In each figure, 1 is a rotor disk and 2 is a moving blade. As shown in FIG. 5, the moving blade 2 is formed with a Christmas tree-shaped leg 2b at the base of the blade stem 2a. On the other hand, a Christmas tree-shaped wing groove 1a corresponding to the shape of the leg portion 2b is engraved in the rotor disk 1 along the outer peripheral edge thereof in the axial direction.

そして、ロータディスク１に動翼２を装着するには、図５のように動翼２の脚部２ｂをロータディスク１の翼溝１ａへ矢印方向から嵌め込んだ上で固定板（不図示）などを介して固定支持される（図４（ａ），（ｂ）参照）。なお、このアキシャルエントリー式の動翼固定構造においては、動翼２の装着，取り外しの組立性を考慮して動翼の脚部２ｂとロータディスク１の翼溝１ａとの間に０．３mm程度のはめ合い隙間Ｇ-1を設定して隙間ばめ
されている。 In order to attach the rotor blade 2 to the rotor disk 1, the leg 2b of the rotor blade 2 is fitted into the blade groove 1a of the rotor disk 1 from the arrow direction as shown in FIG. Etc. (see FIGS. 4A and 4B). In this axial entry type moving blade fixing structure, about 0.3 mm is provided between the moving blade leg 2b and the blade groove 1a of the rotor disk 1 in consideration of assembling / disassembling of the moving blade 2. The fitting gap G-1 is set to fit the gap.

ところで、ロータディスク１に動翼２をアキシャルエントリー式に装着した蒸気タービンのロータでは、前記の嵌め合い隙間Ｇ-1がロータディスク１の軸方向、したがって動翼２を通過する蒸気の通流方向（図４に表した矢印Ｐ）に沿って形成される。しかも、タービン運転時には、動翼２の蒸気流入側と流出側との間に動翼で発生する動力に対応する圧力差が発生することから、前記の嵌め合い隙間Ｇ-1に蒸気またはドレン（蒸気が凝結して液滴化したもの）が侵入するようになる。また、この嵌め合い隙間Ｇ-1に侵入した蒸気，ドレンは蒸気タービンが運転を停止した場合には隙間内部に留まり、蒸気もドレン化して隙間内部に留まることになる。   By the way, in the rotor of the steam turbine in which the rotor blade 1 is attached to the rotor disk 1 in the axial entry type, the fitting gap G-1 is in the axial direction of the rotor disk 1, and thus the flow direction of the steam passing through the rotor blade 2. (Arrow P shown in FIG. 4). Moreover, during turbine operation, a pressure difference corresponding to the power generated by the moving blades is generated between the steam inflow side and the outflow side of the moving blades 2, so that steam or drain ( The vapor condenses into droplets). Further, when the steam turbine stops operating, the steam and drain that have entered the fitting gap G-1 remain inside the gap, and the steam also drains and stays inside the gap.

そのために、地熱井から噴出する地熱流体を気液分離して得た蒸気（湿り蒸気）をタービンに供給して運転する地熱蒸気タービンでは、蒸気に含まれている硫化水素や塩化物イオンなどの腐食性成分が蒸気と一緒に前記の嵌め合い隙間Ｇ-1に侵入する。また、タービンの運転停止時には隙間Ｇ-1の中で蒸気が結露し、蒸気に含まれていた前記腐食性成分がドレン化して前記の翼溝１ａ，脚部２ｂの表面に付着する。この腐食性液は蒸気タービンが再起動，運転停止を繰り返す度に生成されるので、腐食性液は次第に濃縮されてこの部位に堆積してゆく。その結果、動翼２の固定部（植え込み部位）には隙間腐食や腐食疲労，応力腐食割れなどが発生し、最悪の場合には動翼の破断事故に進展するおそれがある。   For this reason, in geothermal steam turbines that operate by supplying steam (wet steam) obtained by gas-liquid separation of geothermal fluid ejected from geothermal wells to the turbine, hydrogen sulfide, chloride ions, etc. contained in the steam Corrosive components enter the fitting gap G-1 together with the steam. Further, when the turbine is stopped, the steam condenses in the gap G-1, and the corrosive component contained in the steam is drained and adheres to the surfaces of the blade groove 1a and the leg 2b. Since this corrosive liquid is generated every time the steam turbine is restarted and shut down, the corrosive liquid is gradually concentrated and accumulates at this site. As a result, crevice corrosion, corrosion fatigue, stress corrosion cracking, and the like occur in the fixed portion (planting site) of the rotor blade 2, and in the worst case, the rotor blade may break.

そこで、前記した動翼固定部の防食対策として、従来ではロータディスク１の翼溝１ａ，および動翼２の脚部２ｂにショットピーニングなどを施す方法のほかに、次記のような合成樹脂材の塗装による防食構造が先に提案されている。
（１）ロータディスク１の翼溝１ａの内面，および動翼２の脚部２ｂの表面にそれぞれ樹脂を個別に塗布して防食層を形成した上で、ロータディスク１の翼溝１ａに動翼２の脚部２ｂを嵌合してアキシャルエントリー式に固定し、先記したはめ合い隙間Ｇ-1を前記防食層によりシールして脚溝／脚部間の嵌め合い隙間Ｇ-1に蒸気が侵入するのを防止する（例えば、特許文献１参照）。
（２）ロータディスク１の蒸気流入側，流出側の端面に閉塞板を配して前記のはめ合い隙間Ｇ-1を両側から塞ぎ、該隙間への蒸気の侵入を防止する（例えば、特許文献２参照）。 Therefore, as a countermeasure against corrosion of the moving blade fixing portion described above, conventionally, in addition to a method of performing shot peening or the like on the blade groove 1a of the rotor disk 1 and the leg portion 2b of the moving blade 2, the following synthetic resin material An anti-corrosion structure by painting has been proposed previously.
(1) A resin is individually applied to the inner surface of the blade groove 1a of the rotor disk 1 and the surface of the leg 2b of the rotor blade 2 to form an anticorrosion layer, and then the rotor blade is inserted into the blade groove 1a of the rotor disk 1 2 leg 2b is fitted and fixed in an axial entry type, and the fitting gap G-1 is sealed by the anticorrosion layer, and steam is generated in the fitting gap G-1 between the leg groove / leg. Intrusion is prevented (see, for example, Patent Document 1).
(2) A closing plate is provided on the steam inflow side and outflow side end faces of the rotor disk 1 to close the fitting gap G-1 from both sides to prevent the vapor from entering the gap (for example, Patent Documents) 2).

特開２００４−２０４７６０号公報JP 2004-204760 A 特開２００５−６９０１８号公報JP-A-2005-69018

ところで、前記した従来の防食対策には次記のような問題点がある。すなわち、
（１）特許文献１のように、刷毛塗り，あるいはディスペンサなどによりロータディスクの翼溝，動翼脚部の表面に樹脂を塗布して防食層を塗布形成するには、ロータディスクの１段落当りの装着枚数が３０枚程度にも及ぶ動翼の個々について樹脂を均一な厚さに塗布し、さらにその塗布状態を検査するのに多大な時間と労力を要し、特にロータディスクに刻設した翼植え込み溝内の狭隘部の塗布作業には困難を伴う。さらに、樹脂塗膜とタービン構成材の密着性が悪い場合、あるいはタービンの運転に伴って発生する遠心力や熱応力により発生する歪みや、ロータディスクの翼溝と動翼の脚部との摺動などにより樹脂塗膜の密着性が低下したり皮膜が損傷，剥離したりして防食層（樹脂塗膜）とタービン構成材とに隙間が発生すると、蒸気に含まれる先記の腐食性成分が嵌め合い隙間Ｇ-1(図４参照)に侵入して隙間腐食を助長することも懸念される。
（２）また、特許文献２のように、ロータディスクの蒸気流入側，流出側の端面に閉塞板を設けてロータディスクの翼溝，動翼脚部の端面を塞ぐようにした防食構造では、ロータディスクの端面に臨む嵌め合い隙間Ｇ-1の開口面は塞がれるものの、ロータディスクの外周面側で隣り合う動翼脚部の相互間に生じる軸方向に沿った隙間Ｇ-2（図４参照）は前記閉塞板で塞ぐことができず、このためにロータディスクの周面側から嵌め合い隙間Ｇ-1に蒸気，ドレンが侵入して高い防食機能を確保することが困難である。なお、特許文献２には閉塞板（動翼固定板）に加えて、ロータディスクの翼溝／動翼の脚部間のはめ合い間隙Ｇ-1を樹脂塗膜で充填するシール方法が開示されているが、この方法は前項（１）と同様な手順で行うため、樹脂の塗布作業，およびその検査工程に多大な時間と労力を要する問題がある。 By the way, the conventional anticorrosion measures described above have the following problems. That is,
(1) As in Patent Document 1, in order to apply and form an anticorrosion layer by applying a resin to the surfaces of rotor blade blade grooves and rotor blade legs by brushing or using a dispenser, etc. For each of the moving blades, the number of which is about 30, the resin was applied to a uniform thickness, and it took a lot of time and labor to inspect the applied state, and was especially engraved on the rotor disk. It is difficult to apply the narrow part in the wing implantation groove. Furthermore, when the adhesion between the resin coating and the turbine components is poor, or the distortion caused by centrifugal force and thermal stress generated during turbine operation, the sliding between the rotor disk blade groove and the rotor blade leg If the adhesion of the resin coating is reduced or the coating is damaged or peeled off due to movement, etc., and there is a gap between the anticorrosive layer (resin coating) and the turbine component, the corrosive component described above contained in the steam There is also a concern that it may enter the fitting gap G-1 (see FIG. 4) and promote crevice corrosion.
(2) Also, as in Patent Document 2, in the anticorrosion structure in which the end face of the rotor disk is provided with a closing plate on the steam inflow side and outflow side end faces to close the end faces of the rotor disk blade grooves and rotor blade legs, Although the opening surface of the fitting gap G-1 facing the end face of the rotor disk is closed, the gap G-2 along the axial direction generated between adjacent rotor blade legs on the outer peripheral surface side of the rotor disk (see FIG. 4) cannot be closed by the closing plate, and for this reason, it is difficult to secure a high anticorrosion function by fitting steam and drain into the fitting gap G-1 from the peripheral surface side of the rotor disk. Patent Document 2 discloses a sealing method in which a fitting gap G-1 between a blade groove / rotor blade leg of a rotor disk is filled with a resin coating in addition to a closing plate (moving blade fixing plate). However, since this method is carried out in the same procedure as in the previous item (1), there is a problem that much time and labor are required for the resin coating operation and the inspection process.

そのほか、地熱タービンでは、地熱流体の蒸気中に塩化物、硫酸塩、土砂類などの固形物のほか、シリカ（SiO2）、カルサイト（CaCO3）などの析出物が含まれており、長期運転に伴いタービン構成材がエロージョン損傷を生じるほどの環境にある。このためタービンのロータディスク，動翼に対して前記のように施される防食皮膜(樹脂塗膜)についても、エロージョン損傷から保護するために耐摩耗性が要求される。 In addition, in geothermal turbines, solids such as chlorides, sulfates and earth and sand, as well as precipitates such as silica (SiO 2 ) and calcite (CaCO 3 ) are contained in the geothermal fluid steam. The turbine components are in an environment that causes erosion damage during operation. For this reason, the anticorrosion coating (resin coating) applied to the rotor disk and rotor blade of the turbine as described above is also required to have wear resistance in order to protect it from erosion damage.

この発明は上記の点に鑑みなされたものであり、その目的はロータディスクの周縁に動翼の翼列をアキシャルエントリー式に装着した蒸気タービンを対象に、簡易な構造，施工法で信頼性の高い防食機能が確保できるように改良したタービンロータの防食構造を提供することにある。   SUMMARY OF THE INVENTION The present invention has been made in view of the above points, and its object is to provide a simple structure and construction method for a steam turbine in which a blade row of moving blades is attached to the periphery of a rotor disk in an axial entry manner. An object of the present invention is to provide an improved anti-corrosion structure for a turbine rotor so as to ensure a high anti-corrosion function.

上記目的を達成するために、この発明によれば、ロータディスクの外周縁に動翼の翼列を固定した蒸気タービンのロータであり、ロータディスクの外周縁に沿って軸方向に刻設した翼植え込み用の翼溝に動翼の脚部を嵌合してアキシャルエントリー式に固定したものにおいて
（１）動翼の翼列をロータディスクに装着した組立状態で、ロータディスクの蒸気流入側，流出側端面に臨む前記翼溝／脚部間の隙間の開口面、および隣り合う動翼の脚部相互間に臨む隙間の開口面を覆って、前記動翼の翼列をロータディスクに装着した組立体の蒸気流入側，流出側端面、および外周面に気体遮蔽性の樹脂を塗布して防食皮膜を被覆形成するものとする（請求項１）。
（２）前項（１）の構成において、防食皮膜の上に耐磨耗性成分を含有する皮膜をコーティングする（請求項２）。
（３）前項（１）の防食皮膜を、気体遮蔽性の樹脂に耐磨耗性成分を分散させた複合樹脂塗膜で形成する（請求項３）。
In order to achieve the above object, according to the present invention, there is provided a rotor of a steam turbine in which a blade row of a moving blade is fixed to the outer peripheral edge of the rotor disk, and the blade engraved in the axial direction along the outer peripheral edge of the rotor disk. (1) In the assembled state where the blade row of the rotor blade is mounted on the rotor disk, the rotor disk steam inflow side, outflow Covering the opening surface of the gap between the blade grooves / legs facing the side end surface and the opening surface of the gap facing between the legs of adjacent blades, the blade row of the blades mounted on the rotor disk A three-dimensional steam inflow side, outflow side end surface, and outer peripheral surface are coated with a gas shielding resin to form an anticorrosion coating (Claim 1).
(2) In the structure of the preceding item (1), a film containing an abrasion-resistant component is coated on the anticorrosive film (Claim 2).
(3) The anticorrosion film of the above item (1) is formed of a composite resin coating film in which an abrasion-resistant component is dispersed in a gas-shielding resin (claim 3).

上記したこの発明の防食構造によれば、動翼をロータディスクに固定したロータ組立状態で動翼固定部の外面周域に気体遮蔽性の樹脂を塗布して防食皮膜を被覆形成することにより、ロータディスクの翼溝／動翼脚部間の嵌め合い隙間、およびロータディスクの外周面上に並ぶ動翼相互間の隙間の開口面を外側からシールして前記隙間に蒸気が侵入するのを防ぐことができる。   According to the above-described anticorrosion structure of the present invention, by applying a gas shielding resin to the outer peripheral area of the rotor blade fixing portion in the rotor assembly state in which the rotor blade is fixed to the rotor disk, The fitting gap between the rotor disk blade groove / blade blade leg and the opening surface of the gap between the rotor blades arranged on the outer peripheral surface of the rotor disk are sealed from the outside to prevent vapor from entering the gap. be able to.

これにより、従来の防食構造(特許文献１)のように動翼をロータディスクに装着する以前の組立前の状態で、あらかじめロータディスクの翼溝内面，および動翼の脚部外面に樹脂材を個別に塗布，塗布面を検査する手間の掛かる労力を省き、簡便，かつ低コストな施工で動翼の固定部に対して信頼性の高い防食機能を確保できる。   As a result, in the state before assembly before attaching the rotor blade to the rotor disk as in the conventional anticorrosion structure (Patent Document 1), the resin material is previously applied to the inner surface of the rotor groove and the outer surface of the leg of the rotor blade. It saves labor and labor to inspect the coating and coating surface individually, and can secure a highly reliable anticorrosion function for the fixed part of the rotor blade by simple and low-cost construction.

また、前記防食皮膜の上に耐磨耗性成分を含有する皮膜をコーティングする、あるいは防食皮膜を気体遮蔽性の樹脂に耐磨耗性成分を分散させた複合樹脂の塗膜で形成することにより、各種固形物，析出物が混入した蒸気流による防食皮膜のエロージョン損傷を防ぐことができて耐久性，信頼性のより一層の向上が図れる。   Also, by coating the anticorrosion film with a film containing an abrasion resistant component, or forming the anticorrosion film with a coating film of a composite resin in which the abrasion resistant component is dispersed in a gas shielding resin. Further, the erosion damage of the anticorrosion film due to the vapor flow mixed with various solids and precipitates can be prevented, and the durability and reliability can be further improved.

この発明の実施例１に係わる防食構造を表す図で、（ａ），（ｂ）はそれぞれ動翼固定部の斜視端面図，および周面図BRIEF DESCRIPTION OF THE DRAWINGS It is a figure showing the anticorrosion structure concerning Example 1 of this invention, (a), (b) is a perspective end view of a moving blade fixing | fixed part, respectively, and a surrounding surface figure この発明の実施例２に係わる防食構造を表す図で、（ａ），（ｂ）はそれぞれ動翼固定部の斜視端面図，および周面図It is a figure showing the anticorrosion structure concerning Example 2 of this invention, (a), (b) is a perspective end view of a moving blade fixing | fixed part, respectively, and a surrounding surface figure この発明の実施例３に係わる防食構造を表す図で、（ａ），（ｂ）はそれぞれ動翼固定部の斜視端面図，および周面図It is a figure showing the anticorrosion structure concerning Example 3 of this invention, (a), (b) is a perspective end view of a moving blade fixing | fixed part, respectively, and a surrounding surface figure ロータディスクに動翼を装着したロータの基本構造図で、（ａ），（ｂ）はそれぞれ動翼固定部の斜視端面図，および周面図The basic structure of a rotor with rotor blades attached to the rotor disk, (a) and (b) are perspective end view and peripheral view of the rotor blade fixing part, respectively. 図４の分解斜視図4 is an exploded perspective view of FIG.

以下、この発明による蒸気タービンのロータの実施の形態を図１〜図３に示す実施例に基づいて説明する。なお、図１，図２，図３はそれぞれ実施例１，実施例２，実施例３に係わるロータの防食構造を表す図であり、各図において図４に対応する部材には同じ符号を付してその説明は省略する。   DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of a steam turbine rotor according to the present invention will be described below based on the embodiments shown in FIGS. 1, 2, and 3 are diagrams showing the anticorrosion structure of the rotor according to Example 1, Example 2, and Example 3, respectively, and members corresponding to those in FIG. The description is omitted.

まず、この発明の請求項１に係わる実施例を図１（ａ），（ｂ）で説明する。この実施例においては、ロータディスク１の翼溝１ａに動翼２の脚部２ｂをアキシャルエントリー式に装着したロータの組立状態で、ロータディスク１の蒸気流入側，流出側端面に開口する嵌め合い隙間Ｇ-1、および隣り合う動翼２の相互間で脚部２ｂの周面に開口する隙間Ｇ-2の開口端面を覆って動翼２の固定部周域の外表面に気体遮断性の樹脂を塗布して防食皮膜５を被覆形成している。なお、５ａはロータディスク１の蒸気流入側，流出側端面に塗布した樹脂塗膜、５ｂは隣り合って並ぶ動翼脚部２ｂの周面に塗布した樹脂塗膜であり、樹脂塗膜５ａは図４における嵌め合い隙間Ｇ-1の開口端面をシールし、樹脂塗膜５ｂは隙間Ｇ-2の開口端面をシールする。これにより、簡易な施工とコストで特許文献１に開示されている防食構造と同等な防食機能を確保することができる。   First, an embodiment according to claim 1 of the present invention will be described with reference to FIGS. In this embodiment, in the assembled state of the rotor in which the leg portion 2b of the rotor blade 2 is attached to the blade groove 1a of the rotor disk 1 in the axial entry manner, the fitting is opened to the steam inflow side and outflow side end faces of the rotor disk 1. The gap G-1 and the outer end surface of the fixed portion of the moving blade 2 that covers the opening end surface of the gap G-2 that opens to the peripheral surface of the leg portion 2b between the adjacent moving blades 2 are gas-blocking. The anticorrosive film 5 is formed by coating a resin. In addition, 5a is a resin coating applied to the steam inflow side and outflow side end surfaces of the rotor disk 1, and 5b is a resin coating applied to the peripheral surface of the adjacent rotor blade leg 2b. The opening end face of the fitting gap G-1 in FIG. 4 is sealed, and the resin coating film 5b seals the opening end face of the gap G-2. Thereby, the anticorrosion function equivalent to the anticorrosion structure currently disclosed by patent document 1 can be ensured by simple construction and cost.

ここで、前記の防食皮膜５は気体遮断性のほかに、タービンの運転温度に相応した耐熱性も要求されることから、防食皮膜５に用いる樹脂としては耐熱性に加えて水蒸気，酸素などの気体に対する透過性の低いポリイミド樹脂が好適である。また、この樹脂を動翼２の固定部周域に塗布するには、ロータ１の翼溝１ａに動翼２の脚部２ｂを嵌合してアキシャルエントリー式に装着した状態で、まず樹脂の塗布面を溶剤にて脱脂した上で、刷毛塗り法などにより前記のポリイミド樹脂を塗布した後、赤外線加熱などにより樹脂塗布面を予備乾燥（温度１５０℃）し、さらに３００℃程度の高温で本加熱してポリイミド樹脂をイミド化して防食皮膜５を形成する。なお、樹脂塗膜の膜厚は特に制約はないが、塗装コストと防食機能とのバランスから膜厚が１００μｍ程度となるように希釈剤にて調整して塗布するのがよい。   Here, in addition to the gas barrier property, the anticorrosion film 5 is required to have heat resistance corresponding to the operating temperature of the turbine. Therefore, the resin used for the anticorrosion film 5 is not only heat resistance but also water vapor, oxygen, etc. A polyimide resin having a low gas permeability is preferable. In addition, in order to apply this resin to the peripheral area of the fixed portion of the rotor blade 2, first, the resin is first fitted with the leg portion 2b of the rotor blade 2 fitted into the blade groove 1a of the rotor 1 and attached in an axial entry manner. After degreasing the coated surface with a solvent, the polyimide resin is coated by a brushing method or the like, and then the resin coated surface is pre-dried (temperature 150 ° C.) by infrared heating or the like, and further heated at a high temperature of about 300 ° C. The anticorrosive film 5 is formed by heating to imidize the polyimide resin. The film thickness of the resin coating film is not particularly limited, but it is preferable that the resin coating film is adjusted and applied with a diluent so that the film thickness is about 100 μm from the balance between the coating cost and the anticorrosion function.

次にこの発明の請求項２に係わる実施例を図２（ａ），（ｂ）に示す。この実施例は先記の実施例１で動翼２の固定部周域に被覆形成した防食皮膜５をエロージョン損傷から保護するようにしたものであり、図示のように防食皮膜５の上に耐磨耗性皮膜６をコーティングしている。なお、６ａはロータディスク２の蒸気流入側，流出側の端面に塗布した皮膜、６ｂは隣り合う動翼２の相互間で脚部２ｂの外周面に塗布した皮膜であり、この耐磨耗性皮膜６は例えばアルミ粉末を含有したセラミック結合体からなる塗料をスプレー塗装した上で、赤外線加熱（３５０℃程度）により焼き付けして耐磨耗性皮膜６（コーティング層）を形成する。   Next, an embodiment according to claim 2 of the present invention is shown in FIGS. In this embodiment, the anticorrosion film 5 formed on the periphery of the fixed portion of the rotor blade 2 in Example 1 is protected from erosion damage. As shown in FIG. The wearable film 6 is coated. In addition, 6a is a film | membrane applied to the end surface of the steam inflow side of the rotor disk 2, and the outflow side, 6b is a film | membrane applied to the outer peripheral surface of the leg part 2b between the adjacent blades 2, and this abrasion resistance For example, the coating 6 is formed by spraying a paint composed of a ceramic combined body containing aluminum powder and then baking by infrared heating (about 350 ° C.) to form the wear-resistant coating 6 (coating layer).

これにより、蒸気中に塩化物、硫酸塩、土砂類などの固形物のほか、シリカ，カルサイトなどの析出物が含まれる地熱蒸気タービンにおいても、動翼２の固定部周域に施された防食皮膜５(図１参照)を、エロージョン損傷から安全に保護することができて信頼性の向上，長寿命化が図れる。   As a result, even in geothermal steam turbines in which solids such as chlorides, sulfates, earth and sand, as well as precipitates such as silica and calcite are contained in the steam, they are applied to the periphery of the fixed part of the rotor blade 2. The anticorrosion coating 5 (see FIG. 1) can be safely protected from erosion damage, improving reliability and extending the life.

図３（ａ），（ｂ）はこの発明の請求項３に係わる実施例を示すものである。この実施例では、先記の実施例１で述べた防食皮膜の樹脂材として、気体遮蔽性と耐磨耗性の両方の機能を合わせ持つ複合樹脂を用い、この複合樹脂を動翼２の固定部周域、すなわちロータディスク１の蒸気流入側，流出側の端面、および隣り合う動翼２の相互間で脚部２ｂの外周面にそれぞれ塗布（塗膜７ａ，７ｂ）して複合樹脂塗膜(防食皮膜)７を形成する。なお、この複合樹脂としては、例えばポリアミドイミドにグラファイトの粉末を分散させた塗料が挙げられる。   3A and 3B show an embodiment according to claim 3 of the present invention. In this embodiment, as the resin material of the anticorrosion film described in the first embodiment, a composite resin having both functions of gas shielding and wear resistance is used, and this composite resin is fixed to the moving blade 2. The composite resin coating is applied to the outer circumferential surface of the leg 2b between the peripheral areas, that is, the end surfaces on the steam inflow side and the outflow side of the rotor disk 1 and the adjacent rotor blades 2 respectively. (Anti-corrosion film) 7 is formed. An example of the composite resin is a paint in which graphite powder is dispersed in polyamideimide.

この実施例によれば、動翼２の固定部周域の表面に前記の複合樹脂を１層被覆形成するだけの簡易な施工で、先記実施例２と同等な耐磨耗性の高い気体遮蔽性の防食皮膜７を形成してエロージョン損傷からも安全に保護することができる。   According to this embodiment, the gas having a high wear resistance equivalent to that of the above-mentioned embodiment 2 can be obtained by a simple construction in which the single layer of the composite resin is formed on the surface of the fixed portion of the moving blade 2. By forming the shielding anticorrosive film 7, it can be safely protected from erosion damage.

１ ロータディスク
１ａ 翼溝
２ 動翼
２ａ 翼幹
２ｂ 脚部
３ ロータディスクの蒸気流入側端面
４ ロータディスクの蒸気流出側端面
５ 防食皮膜（気体遮蔽性の樹脂塗膜）
６ 耐磨耗性皮膜（コーティング層）
７ 複合樹脂塗膜(防食皮膜) DESCRIPTION OF SYMBOLS 1 Rotor disk 1a Blade groove 2 Rotor blade 2a Blade trunk 2b Leg part 3 End face of steam inlet side of rotor disk 4 End face of steam outlet side of rotor disk 5 Anticorrosion coating (gas shielding resin coating)
6 Abrasion-resistant film (coating layer)
7 Composite resin coating (corrosion protection coating)

Claims (3)

ロータディスクの外周縁に動翼の翼列を装着した蒸気タービンのロータであり、ロータディスクの外周縁に沿って軸方向に刻設した翼植え込み用の翼溝に動翼の脚部を嵌合してアキシャルエントリー式に固定したものにおいて、
動翼の翼列をロータディスクに装着した組立状態で、ロータディスクの蒸気流入側，流出側端面に臨む前記翼溝／脚部間の隙間、および隣り合う動翼の脚部相互間に臨む隙間の開口面を覆って、前記動翼の翼列をロータディスクに装着した組立体の蒸気流入側，流出側端面、および外周面に気体遮蔽性の樹脂を塗布して防食皮膜を被覆形成したことを特徴とする蒸気タービンのロータ。 This is a steam turbine rotor with a rotor blade cascade mounted on the outer periphery of the rotor disk, and the legs of the rotor blade are fitted into the blade groove for blade implantation engraved in the axial direction along the outer periphery of the rotor disk. In what is fixed to the axial entry type,
The gap between the blade grooves / legs facing the steam inflow side and outflow side end faces of the rotor disk and the gaps between the adjacent rotor blade legs when the blade row of the rotor blades is mounted on the rotor disk. An anti-corrosion coating was formed by coating a gas shielding resin on the steam inflow side, outflow side end face, and outer peripheral surface of the assembly in which the blade row of the rotor blade was mounted on the rotor disk. A rotor of a steam turbine characterized by the above. 請求項１に記載の蒸気タービンのロータにおいて、防食皮膜の上に耐磨耗性成分を含有する皮膜をコーティングしたことを特徴とする蒸気タービンのロータ。   2. The steam turbine rotor according to claim 1, wherein a coating containing an abrasion-resistant component is coated on the anticorrosion coating. 請求項１に記載の蒸気タービンのロータにおいて、防食皮膜が気体遮蔽性の樹脂に耐磨耗性成分を分散させた複合樹脂塗膜であることを特徴とする蒸気タービンのロータ。   2. The steam turbine rotor according to claim 1, wherein the anticorrosion coating is a composite resin coating in which a wear-resistant component is dispersed in a gas shielding resin.
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US10858946B2 (en) 2013-12-06 2020-12-08 Safran Helicopter Engines Bladed rotor

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JP5413212B2 (en) * 2010-01-21 2014-02-12 富士電機株式会社 Steam turbine rotor and method of manufacturing steam turbine rotor
US10047614B2 (en) * 2014-10-09 2018-08-14 Rolls-Royce Corporation Coating system including alternating layers of amorphous silica and amorphous silicon nitride
JP6785555B2 (en) * 2016-01-15 2020-11-18 三菱パワー株式会社 How to assemble the rotor blade to the turbine rotor

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