JP2004174580A - Structure and method for brazing machinable sealant - Google Patents

Structure and method for brazing machinable sealant Download PDF

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JP2004174580A
JP2004174580A JP2002345539A JP2002345539A JP2004174580A JP 2004174580 A JP2004174580 A JP 2004174580A JP 2002345539 A JP2002345539 A JP 2002345539A JP 2002345539 A JP2002345539 A JP 2002345539A JP 2004174580 A JP2004174580 A JP 2004174580A
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brazing
machinable
stop
sealing material
base material
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JP4176454B2 (en
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Minoru Ohara
稔 大原
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Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
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Abstract

<P>PROBLEM TO BE SOLVED: To provide a structure and a method for brazing a machinable sealant for preventing degradation of machinability. <P>SOLUTION: A stop-off area for preventing infiltration of brazing filler metal is provided to a predetermined depth on a non-brazing surface side of a honeycomb seal 1 via a step of masking an area to a predetermined depth on a brazing surface side by penetrating the brazing surface side of the honeycomb seal 1 which is a machinable sealant to a masking sheet 12, a step of forming a film 13a of a stop-off agent on other area than a masking area by depositing the stop-off agent 13 on the honeycomb seal 1 in this condition, a step of removing a masking sheet 12 after the previous step, a step of mounting a surface to be brazed of the honeycomb seal 1 on a sheet of a brazing filler metal 7 disposed on a base material 10 in a penetrating manner after the previous step, and a step of placing the honeycomb seal 1 and the base material 10 after the previous step in a heating furnace 9, and brazing them. <P>COPYRIGHT: (C)2004,JPO

Description

【０００１】
【発明の属する技術分野】
本発明は、例えばタービンのケーシング側の内壁面に対し、タービン動翼に対向するよう設けられる被削性シール材のろう付け構造と、そのろう付け方法とに関する。
【０００２】
【従来の技術】
この種の被削性シール材は、タービン動翼側から見た場合にハニカム構造となっているように見えるので、一般的にハニカムシールと呼ばれている。
【０００３】
ハニカムシールは、ガスタービンの後方動翼の相手側に位置するケーシング側の分割環の内周面に貼り付けられる薄肉板状のシール材であり、タービン動翼と分割環との間の隙間をシールしている。また、このハニカムシールは、良好な被削性（削られ易さ）を有するように形成されており、タービン動翼の先端が何らかの原因（熱膨脹等）で接触した際に自らの表面が削られることで、接触によるタービン動翼と分割環の損傷を防止している（特許文献１、特許文献２参照）。
【０００４】
図６は、ハニカムシールの概略構成を拡大して示しており、図７は、図６のＶＩ−ＶＩ矢視断面を示している。図６において、１はハニカムシールであり、ケーシング側の部材（分割環等）である基材１０の上面にろう付けにより固定されている。ハニカムシール１は、板面に垂直なＡ方向の被削性と板面に平行な特定のＢ方向のシール性を持たせるために、空所と隔壁よりなる蜂の巣状の小室区画構造を持った板状体として形成されている。符号３は蜂の巣（ハニカム）状の多数のセル（小室区画）を示す。
【０００５】
このハニカムシール１は、ハニカム状のセル３を、基盤１０の板面に対して垂直なＡ方向に立てた複数枚の波形薄板２の組み合わせにより形成している関係上、各波形薄板２同士の重合部４に微小隙間５を有している。なお、シール性を発揮するＢ方向は、波形薄板２の延設方向と直交している。
【０００６】
このような構造のハニカムシール１を基材１０に対してろう付けする場合は、図８に示す工程に沿って作業を進める。まず、同図（ａ）に示すように基材１０の上に各波形薄板２を組み合わて構成したハニカムシール１を載せ、スポット溶接で仮固定する。
【０００７】
次に、同図（ｂ）に示すように、ハニカムシール１の上からろう材７の粉末を振りかけて、前記各セル３（小室区画）に落とし込み、基材１０の上にろう材７の粉末をむらなく敷き詰める。あるいは、同図（ｃ）及び（ｄ）に示すように、バインダでろう材７をシート状にしたものを、ハニカムシール１の上に載せて、アセトン８で溶かして前記各セル３に落とし込む。
【０００８】
次いで、同図（ｅ）に示すように、それを加熱炉９に入れてハニカムシール１を基材１０に対してろう付け接合する。
【０００９】
【特許文献１】
特開平１１−６４４６号公報
【特許文献２】
特開平１１−１３４０４号公報
【００１０】
【発明が解決しようとする課題】
ところで、ハニカムシール１は、タービン動翼に対向する面側に良好な被削性を備えることが製品としての条件であるが、上述のようにろう付けした際に、不具合が生じる虞を有している。
【００１１】
すなわち、ハニカムシール１は、前述したように複数の波形薄板２の組み合わせで構成されている関係上、波形薄板２同士の重合部４に微小隙間５を有している。この微小隙間５は、基盤１０の板面に対して垂直なＡ方向に延びており、基材１０にハニカムシール１をろう付けするとき、図６に示すように、その微小隙間５にろう材７が毛細管現象で浸透してハニカムシール１の剛性が増大し、結果として、同領域の被削性が低下する虞がある。このように被削性が低下してしまうと、タービン動翼側の損耗が激しくなるので、ハニカムシール１としての機能を発揮することができない。
【００１２】
本発明は、上記事情に鑑みてなされたものであり、被削性の低下を生じることのない被削性シール材のろう付け構造と、そのろう付け方法とを提供することを目的とする。
【００１３】
【課題を解決するための手段】
本発明は、上記課題を解決するために以下の手段を採用した。
すなわち、請求項１記載の被削性シール材のろう付け構造は、複数枚の波形薄板を重ね合わせて空所と隔壁よりなる蜂の巣状の小室区画構造を持った板状体をなし、基材側に対して固定されることで該基材及び回転体間の隙間をシールし、前記回転体が接触した場合に自らが削られる被削性シール材を、前記基材に対してろう付けする構造において、前記被削性シール材の非ろう付け面側の所定深さまで、ろう材の浸透を阻止したストップオフ領域を設けたことを特徴とする。
【００１４】
上記請求項１に記載の被削性シール材のろう付け構造によれば、被削性シール材の非ろう付け面側の所定深さまで、ろう材の浸透を阻止したストップオフ領域を設けているので、この領域までろう材が浸透してくるのを防ぐことができる。
【００１５】
請求項２に記載の被削性シール材のろう付け方法は、複数枚の波形薄板を重ね合わせて空所と隔壁よりなる蜂の巣状の小室区画構造を持った板状体をなし、基材側に対して固定されることで該基材及び回転体間の隙間をシールし、前記回転体が接触した場合に自らが削られる被削性シール材を、前記基材に対してろう付けする方法において、前記被削性シール材の一方の面をなす非ろう付け面側の所定深さまで、ろう材の浸透を阻止するストップオフ領域を確保し、その後、前記被削性シール材の他方の面を前記基材に対してろう付けすることを特徴とする。
【００１６】
上記請求項２に記載の被削性シール材によれば、被削性シール材の非ろう付け面側の所定深さまで、ろう材の浸透を阻止したストップオフ領域を設けているので、この領域までろう材が浸透してくるのを防ぐことができる。
【００１７】
請求項３の発明は、請求項２に記載の被削性シール材のろう付け方法において、前記被削性シール材のろう付け面側をマスキングシートに刺し込むことで、前記ストップオフ領域以外の領域をマスキングする工程と、該工程後の前記被削性シール材にストップオフ剤を付着させることで、前記ストップオフ領域にストップオフ剤の膜を形成する工程と、該工程後の前記被削性シール材から前記マスキングシートを除去する工程と、該工程後の前記被削性シール部材のろう付け面側を前記基材に重ね合わせ、これらの間にろう材を配置する工程と、該工程後の前記被削性シール材及び前記基材を加熱してろう付け処理する工程と、を備えることを特徴とする。
【００１８】
上記請求項３に記載の被削性シール材のろう付け方法によれば、マスキングシートへの被削性シール材の刺し込みによりマスキング領域を確保した上で、ストップオフ剤の膜を被削性シール材の表面に形成するので、ストップオフ領域を精度良くかつ確実に確保することができる。従って、ろう付けした際に、ストップオフ領域へのろう材の浸透を確実に抑止することができる。
【００１９】
請求項４に記載の被削性シール材のろう付け方法は、請求項３に記載の被削性シール材のろう付け方法において、前記ろう材としてシート状のろう材（例えば米国Ｗａｌｌ Ｃｏｌｍｏｎｙ社のＮｉｃｒｏｂｒａｚｅ ＬＭ ｔｒａｎｓｆｅｒ ｔａｐｅ （Ｂｎｉ−２）などが適している。）を用い、 このシート状のろう材を、前記ろう材を配置する工程で、前記基材及び前記被削性シール部材間に挟み込んで行うことを特徴とする。
【００２０】
上記請求項４に記載の被削性シール材のろう付け方法によれば、ろう材を均一に基材に供給することができ、ろう付けのバラツキが少なくなる。また、欠陥（ろう切れ）の発生が減る利点も得られる。
【００２１】
【発明の実施の形態】
以下、本発明の一実施形態を、図面を参照しながら説明する。
【００２２】
図３に示すように、ハニカムシール１は、回転体であるタービン動翼（図示せず）に対向するケーシング側の基材（分割環等）１０の上面（内周面）にろう付けにより固定されている。ハニカムシール１は、基材１０の板面に垂直なＡ方向の被削性と、同板面に平行なＢ方向のシール性とを持たせるために、空所と隔壁よりなる蜂の巣状の小室区画構造を持った板状体として形成されており、同図の符号３は、蜂の巣（ハニカム）状の多数のセル（小室区画）を示す。
【００２３】
このハニカムシール１は、ハニカム状のセル３を、板面に垂直なＡ方向に立てた複数枚の波形薄板２の組み合わせによって形成している関係上、各波形薄板２同士の重合部４に微小隙間５を有している。なお、シール性を発揮するＢ方向は、波形薄板２の延設方向と直交している。
【００２４】
このハニカムシール１を基材１０にろう付けする場合は、図１に示す工程順に作業を進める。
まず、図１（ａ）、（ｂ）に示すように、ハニカムシール１の厚さの半分程度の肉厚を有する柔らかいシリコン樹脂製のマスキングシート１２に、ハニカムシール１のろう付け面側を刺し込むことで、ろう付け面側の所定深さまでの領域をマスキングする。このようにハニカムシール１をマスキングシート１２に刺し込むことにより、ハニカムシール１の微小隙間５にまで樹脂が入り込み、その樹脂がハニカムシール１との接触表面を覆う。この場合のマスキングシート１２としては、ミクロン単位の隙間に侵入し、しかも離型性に優れていることが必要であり、例えば、丸本ストルアス株式会社の「レプリセット」などが好適である。
【００２５】
次に、同図（ｃ）に示すように、マスキングシート１２に刺し込んだままのハニカムシール１を、ストップオフ剤１３を蓄えた貯槽に浸漬させ、ハニカムシール１にストップオフ剤１３を付着させることで、（ｄ）のようにマスキング領域以外の領域にストップオフ剤の膜１３ａを形成する。この浸漬時間としては、例えば５〜１０秒の短時間で十分である。ストップオフ剤１３は、ろう材に対する濡れ性を低減して、ろう材の浸透を防止する役目を果たすものであり、作業後の除去性を考慮して、例えば、ニクロブレーズ社製のホワイトストップオフのタイプ２（水溶性。エアブロー＋水洗いで殆ど除去することが可能。）等を好適に用いることができる。また、ストップオフ剤１３の粘度は、新品時のものと同一になるようにするが、時間がたって粘度が高くなってしまったものを用いる場合には、新品時の粘度と同様になるように、アルコールかアセトンで薄めてから用いることが好ましい。また、浸漬する際のストップオフ剤１３の液面高さとしては、ハニカムシール１の底面を基準として約１ｍｍ程度にすると良い。
【００２６】
このようにしてストップオフ剤１３に浸漬したハニカムシール１を、ストップオフ剤１３から取り出し、その上方から顕微鏡を用いて検査して、重合部４の微小隙間５にストップオフ剤１３が浸透しているかをチェックする。
各セル３内にはストップオフ剤１３が入り込まないことが望ましいので、ハニカムシール１を、そのろう付け面が上方を向くようにしてキムワイプ（図示せず）上に置き、各セル３内に入り込んでいるストップオフ剤１３のみを除去する。その後、半日ほど自然乾燥させる。
【００２７】
次に、同図（ｅ）に示すように、ハニカムシール１からマスキングシート１２を除去し、同図（ｆ）、（ｇ）に示すようにハニカムシール１のろう付け面側を基材１０上に載せる。この際、基材１０の上面に予めろう材７のシートを載せておき、その上にハニカムシール１を刺し込むように載せる。そうすることで、ハニカムシール１のろう付け面と接触する基材１０の上面との間にろう材７を均等配置することができる。
【００２８】
なお、上記図１（ａ）〜（ｄ）の工程では、マスキングする場合を例に説明したが、代わりに図２（ａ）〜（ｄ）の工程を行うことで、マスキングせずに、ろう材７をハニカムシール１に取り付けることが可能となる。
すなわち、図２（ａ）に示すように、ハニカムシール１のろう付け面側が上面となるように載置し、その上にろう材７、続いてビニールシート５０を重ね合わせてから、ドライヤー５１などを用いてビニールシート５０の上から熱風を当てて加熱する。これにより、ろう材７を柔らかくしてハニカムシール１に刺し込みやすくなる。その後、図２（ｂ）に示すように、ビニールシート５０の上から木片等の柔らかい部材５２を用いてろう材７を押さえ込む。この時、図２（ｃ）に示すように、ろう材７の表面にハニカムシール１のハニカム形状が模様としてうっすらと現れるまで押さえ込むようにする。
【００２９】
続いて、ハニカムシール１の母材が基材１０に対してしっかりと密着するように、カッターナイフ等の切削工具を用いて余分なろう材７をそぎ落とし、ハニカム状の母材を露出させる。
続いて、図２（ｄ）に示すように、ハニカムシール１の表面側（ろう付け面と反対側）をワイヤブラシ５３などで擦り、付着しているストップオフ剤１３を取り除く。これにより、スポット溶接時における通電障害を防止することが可能となる。
【００３０】
再び図１（ｈ）に戻って説明を続けると、スポット溶接によりハニカムシール１を基材１０に対して仮固定し、それを同図（ｉ）のように加熱炉９に入れてろう付け処理を行う。そして、同図（ｊ）のように加熱炉から取り出したハニカムシール１に、水をかけたりエアーブローをかけたりすることで、ストップオフ剤の膜１３ａを除去し、同図（ｋ）のように製品としてのハニカムシール１のろう付け構造を得る。
【００３１】
このような各工程を経ることで、図３及び図４に示すように、ハニカムシール１の非ろう付け面側の所定深さまで、ろう材７の浸透を阻止したストップオフ領域Ｈ１を確保することができる。つまり、微小隙間５があるにも拘わらず、その微小隙間５に対して、ある高さまでしかろう材７が上って来ないようにすることができる。なお、図３中のハッチングで施した部分は、図４に示すろう材７が浸透した高さ領域Ｈ２を表している。
【００３２】
このように、削られるべき側の所定深さまでの領域をストップオフ領域Ｈ１として確保しているので、ろう付けした場合にも良好な被削性を維持することができる。
また、基材１０上へのろう材７の配置を、上述のように、シート状のろう材７を使用して行った場合、ろう材７を均一に基材１０の上面に供給することができるので、ろう付けのバラツキが少なくなり、欠陥（ろう切れ）の発生が減る。
【００３３】
なお、基材１０へのろう材７の配置は、図５に示す他の実施形態のように、同図（ｆ）でろう材７の粉末を振りかけることで行ってもよい。この実施形態における他の工程は、図１及び図２に示した他の工程と全く同じであるので、説明は省略する。
【００３４】
【発明の効果】
本発明の請求項１に記載の被削性シール材のろう付け構造によれば、ストップオフ領域を有するものであるため、ろう材の浸透による被削性の低下を防止することが可能となる。
【００３５】
本発明の請求項２に記載の被削性シール材のろう付け方法によれば、ろう付け前の被削性シール材に対してストップオフ領域を確保することができるため、ろう材の浸透による被削性の低下を防止することが可能となる。
【００３６】
また、請求項３に記載の被削性シール材のろう付け方法によれば、ストップオフ領域を精度良くかつ確実に確保することができるので、ろう付けした際に、ストップオフ領域へのろう材の浸透を確実に抑止することが可能となる。
【００３７】
また、請求項４に記載の被削性シール材のろう付け方法によれば、基材にろう材を配置する際に、ろう付けのバラツキを少なくすることが可能となる。
【図面の簡単な説明】
【図１】本発明の被削性シール材のろう付け方法の一実施形態を示す工程説明図である。
【図２】同実施形態の一部変形例を示す工程説明図である。
【図３】図１の工程順に処理を進めることで得られたハニカムシールのろう付け構造の概略斜視図である。
【図４】図３のＩＩＩ−ＩＩＩ矢視断面図である。
【図５】本発明の被削性シール材のろう付け方法の他の実施形態を示す工程説明図である。
【図６】従来の被削性シール材のろう付け構造の概略斜視図である。
【図７】図６のＶＩ−ＶＩ矢視断面図である。
【図８】従来の被削性シール材のろう付け方法の工程説明図である。
【符号の説明】
１ ハニカムシール（被削性シール材）
２ 波形薄板
３ 小室区画
４ 重合部
５ 微小隙間
７ ろう材
９ 加熱炉
１０ 基材
１２ マスキングシート
１３ ストップオフ剤
１３ａ ストップオフ剤の膜
Ｈ１ ストップオフ領域[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to a brazing structure of a machinable sealing material provided to face, for example, a turbine rotor blade to an inner wall surface on a casing side of a turbine, and a brazing method thereof.
[0002]
[Prior art]
This kind of machinable seal material is generally called a honeycomb seal because it appears to have a honeycomb structure when viewed from the turbine blade side.
[0003]
The honeycomb seal is a thin plate-shaped sealing material attached to the inner peripheral surface of the split ring on the casing located on the other side of the rear blade of the gas turbine, and removes a gap between the turbine blade and the split ring. Sealed. Further, this honeycomb seal is formed so as to have good machinability (easiness of shaving), and its surface is shaved when the tip of the turbine blade comes into contact with the blade for some reason (such as thermal expansion). This prevents damage to the turbine blade and the split ring due to contact (see Patent Documents 1 and 2).
[0004]
FIG. 6 shows an enlarged schematic configuration of the honeycomb seal, and FIG. 7 shows a cross section taken along the line VI-VI in FIG. In FIG. 6, reference numeral 1 denotes a honeycomb seal, which is fixed to the upper surface of a base member 10 which is a member (a split ring or the like) on the casing side by brazing. The honeycomb seal 1 has a honeycomb-shaped small chamber partition structure including a cavity and a partition wall so as to have machinability in the direction A perpendicular to the plate surface and sealability in the specific B direction parallel to the plate surface. It is formed as a plate. Reference numeral 3 denotes a number of cells (compartment compartments) in a honeycomb shape.
[0005]
The honeycomb seal 1 has a honeycomb cell 3 formed by a combination of a plurality of corrugated thin plates 2 erected in the direction A perpendicular to the plate surface of the base 10. The overlapping portion 4 has a minute gap 5. In addition, the B direction which exhibits a sealing property is orthogonal to the extending direction of the corrugated thin plate 2.
[0006]
When the honeycomb seal 1 having such a structure is brazed to the base material 10, the operation proceeds according to the process shown in FIG. First, as shown in FIG. 1A, a honeycomb seal 1 composed of a combination of corrugated thin plates 2 is placed on a base material 10 and temporarily fixed by spot welding.
[0007]
Next, as shown in FIG. 3B, the powder of the brazing material 7 is sprinkled from above the honeycomb seal 1 and dropped into each of the cells 3 (compartment compartments). Spread evenly. Alternatively, as shown in FIGS. 3 (c) and 3 (d), a sheet made of the brazing material 7 with a binder is placed on the honeycomb seal 1, melted with acetone 8, and dropped into the cells 3.
[0008]
Next, as shown in FIG. 1E, the honeycomb seal 1 is put into a heating furnace 9 and the honeycomb seal 1 is brazed to the base material 10.
[0009]
[Patent Document 1]
JP-A-11-6446 [Patent Document 2]
JP-A-11-13404
[Problems to be solved by the invention]
By the way, the honeycomb seal 1 is required to have good machinability on the surface side facing the turbine rotor blade as a product, but there is a possibility that a problem may occur when brazing as described above. ing.
[0011]
That is, since the honeycomb seal 1 is constituted by the combination of the plurality of corrugated thin plates 2 as described above, the honeycomb seal 1 has the minute gap 5 in the overlapping portion 4 between the corrugated thin plates 2. The minute gap 5 extends in the direction A perpendicular to the plate surface of the base 10, and when the honeycomb seal 1 is brazed to the substrate 10, as shown in FIG. 7 penetrates by a capillary phenomenon, and the rigidity of the honeycomb seal 1 increases, and as a result, the machinability of the region may be reduced. If the machinability decreases in this way, the wear on the turbine rotor blade side becomes severe, so that the function as the honeycomb seal 1 cannot be exhibited.
[0012]
The present invention has been made in view of the above circumstances, and has as its object to provide a brazing structure for a machinable sealing material that does not cause a decrease in machinability, and a brazing method thereof.
[0013]
[Means for Solving the Problems]
The present invention employs the following means in order to solve the above problems.
In other words, the brazing structure for a machinable sealing material according to claim 1 forms a plate-like body having a honeycomb-shaped small chamber defined by cavities and partition walls by laminating a plurality of corrugated thin plates. The gap between the substrate and the rotating body is sealed by being fixed to the side, and a machinable sealing material which is cut by itself when the rotating body comes into contact is brazed to the substrate. The structure is characterized in that a stop-off region for preventing penetration of the brazing material is provided up to a predetermined depth on the non-brazing surface side of the machinable sealing material.
[0014]
According to the brazing structure for a machinable sealing material according to the first aspect, the stop-off region is provided to prevent the penetration of the brazing material to a predetermined depth on the non-brazing surface side of the machinable sealing material. Therefore, it is possible to prevent the brazing material from permeating into this region.
[0015]
A brazing method for a machinable sealing material according to claim 2, wherein a plurality of corrugated thin plates are overlapped to form a plate-like body having a honeycomb-shaped small chamber defined by cavities and partition walls, and the base material side is formed. A method of brazing a machinable sealing material, which is cut by itself when the rotating body comes into contact with the base material, by sealing a gap between the substrate and the rotating body by being fixed to the base material. In the above, to a predetermined depth of the non-brazing surface side forming one surface of the machinable sealing material, to secure a stop-off region for preventing the penetration of the brazing material, and then, the other surface of the machinable sealing material Is brazed to the base material.
[0016]
According to the machinable sealing material according to the second aspect, the stop-off region that prevents the penetration of the brazing material is provided up to a predetermined depth on the non-brazing surface side of the machinable sealing material. It is possible to prevent the brazing material from penetrating.
[0017]
According to a third aspect of the present invention, in the method for brazing a machinable seal material according to the second aspect, the brazing surface side of the machinable seal material is pierced into a masking sheet to thereby provide a portion other than the stop-off region. Masking an area, forming a film of a stop-off agent in the stop-off area by attaching a stop-off agent to the machinable sealing material after the step, and Removing the masking sheet from the volatile sealing material, superposing the brazing surface side of the machinable sealing member after the process on the base material, and disposing a brazing material therebetween. Heating the brazed seal material and the base material and performing a brazing process.
[0018]
According to the method for brazing a machinable sealing material according to the third aspect, the masking area is secured by piercing the machinable sealing material into the masking sheet, and then the film of the stop-off agent is formed into a machinable sheet. Since the stop-off region is formed on the surface of the sealing material, the stop-off region can be accurately and reliably secured. Therefore, at the time of brazing, penetration of the brazing material into the stop-off region can be reliably suppressed.
[0019]
The method of brazing a machinable seal material according to claim 4 is the method of brazing a machinable seal material according to claim 3, wherein the brazing material is a sheet-like brazing material (for example, a product of Wall Colony, USA). Microbraze LM transfer tape (Bni-2) or the like is suitable.) In the step of disposing the brazing material, the sheet-shaped brazing material is sandwiched between the base material and the machinable sealing member. It is characterized by performing.
[0020]
According to the method for brazing a machinable sealing material according to the fourth aspect, the brazing material can be uniformly supplied to the base material, and variations in brazing are reduced. Further, there is obtained an advantage that occurrence of defects (brazing) is reduced.
[0021]
BEST MODE FOR CARRYING OUT THE INVENTION
Hereinafter, an embodiment of the present invention will be described with reference to the drawings.
[0022]
As shown in FIG. 3, the honeycomb seal 1 is fixed to the upper surface (inner peripheral surface) of a casing-side base material (a split ring or the like) 10 facing a turbine rotor blade (not shown) as a rotating body by brazing. Have been. The honeycomb seal 1 has a honeycomb-shaped small chamber formed of voids and partition walls in order to have machinability in the direction A perpendicular to the plate surface of the base material 10 and sealing properties in the direction B parallel to the plate surface. It is formed as a plate-like body having a partitioned structure, and reference numeral 3 in the figure indicates a number of cells (compartment compartments) in a honeycomb shape.
[0023]
The honeycomb seal 1 has a honeycomb cell 3 formed by a combination of a plurality of corrugated thin plates 2 erected in the direction A perpendicular to the plate surface. There is a gap 5. In addition, the B direction which exhibits a sealing property is orthogonal to the extending direction of the corrugated thin plate 2.
[0024]
When the honeycomb seal 1 is brazed to the base material 10, the operation proceeds in the order of steps shown in FIG.
First, as shown in FIGS. 1A and 1B, the brazing surface side of the honeycomb seal 1 is pierced into a soft silicone resin masking sheet 12 having a thickness of about half the thickness of the honeycomb seal 1. This masks the region up to a predetermined depth on the brazing surface side. By piercing the honeycomb seal 1 into the masking sheet 12 as described above, the resin enters the minute gap 5 of the honeycomb seal 1, and the resin covers the contact surface with the honeycomb seal 1. As the masking sheet 12 in this case, it is necessary that the masking sheet 12 penetrates into a gap of a micron unit and has excellent releasability. For example, “Reset” of Marumoto Struers Co., Ltd. is suitable.
[0025]
Next, as shown in FIG. 1C, the honeycomb seal 1 pierced into the masking sheet 12 is immersed in a storage tank storing the stop-off agent 13, and the stop-off agent 13 is attached to the honeycomb seal 1. As a result, a film 13a of the stop-off agent is formed in a region other than the masking region as shown in FIG. As the immersion time, a short time of, for example, 5 to 10 seconds is sufficient. The stop-off agent 13 serves to reduce the wettability to the brazing material and to prevent the penetration of the brazing material. In consideration of the removability after the work, for example, a white stop-off manufactured by Nicro Blaze Co., Ltd. Type 2 (water-soluble, which can be almost removed by air blowing and washing with water) or the like can be suitably used. In addition, the viscosity of the stop-off agent 13 is set to be the same as that at the time of a new product, but when a product whose viscosity has increased over time is used, the viscosity becomes the same as that at the time of a new product. It is preferable to use it after diluting with alcohol or acetone. The liquid level of the stop-off agent 13 during immersion is preferably about 1 mm with respect to the bottom surface of the honeycomb seal 1.
[0026]
The honeycomb seal 1 immersed in the stop-off agent 13 in this manner is taken out from the stop-off agent 13, inspected from above using a microscope, and the stop-off agent 13 penetrates into the minute gaps 5 in the overlapping portion 4. Check if it is.
Since it is desirable that the stop-off agent 13 does not enter each cell 3, the honeycomb seal 1 is placed on a Kimwipe (not shown) with its brazing surface facing upward, and enters the cell 3. Only the stop-off agent 13 is removed. Then, let it air dry for about half a day.
[0027]
Next, as shown in FIG. 2E, the masking sheet 12 is removed from the honeycomb seal 1, and the brazing surface side of the honeycomb seal 1 is placed on the base material 10 as shown in FIGS. Put on. At this time, a sheet of the brazing material 7 is placed on the upper surface of the base material 10 in advance, and the honeycomb seal 1 is placed on the sheet so as to pierce the sheet. By doing so, the brazing material 7 can be evenly arranged between the brazing surface of the honeycomb seal 1 and the upper surface of the base material 10 in contact with the brazing surface.
[0028]
In the steps of FIGS. 1A to 1D, the case of masking has been described as an example. However, by performing the steps of FIGS. 2A to 2D instead, masking is performed without masking. The material 7 can be attached to the honeycomb seal 1.
That is, as shown in FIG. 2 (a), the honeycomb seal 1 is placed so that the brazing surface side is the upper surface, and the brazing material 7 and the vinyl sheet 50 are overlaid thereon, and then the dryer 51 and the like. Then, hot air is applied from above the vinyl sheet 50 to heat it. As a result, the brazing material 7 is softened and easily pierced into the honeycomb seal 1. Thereafter, as shown in FIG. 2B, the brazing material 7 is pressed down from above the vinyl sheet 50 using a soft member 52 such as a piece of wood. At this time, as shown in FIG. 2C, the honeycomb seal 1 is pressed down until the honeycomb shape of the honeycomb seal 1 slightly appears on the surface of the brazing material 7 as a pattern.
[0029]
Subsequently, using a cutting tool such as a cutter knife, excess brazing material 7 is scraped off so that the base material of the honeycomb seal 1 firmly adheres to the base material 10 to expose the honeycomb-shaped base material.
Subsequently, as shown in FIG. 2D, the surface side (the side opposite to the brazing surface) of the honeycomb seal 1 is rubbed with a wire brush 53 or the like, and the attached stop-off agent 13 is removed. Thereby, it is possible to prevent an energization failure during spot welding.
[0030]
Returning to FIG. 1H again, the explanation is continued. The honeycomb seal 1 is temporarily fixed to the base material 10 by spot welding, and the honeycomb seal 1 is put into a heating furnace 9 as shown in FIG. I do. Then, the film 13a of the stop-off agent is removed by spraying water or air blow on the honeycomb seal 1 taken out of the heating furnace as shown in FIG. Next, a brazing structure for the honeycomb seal 1 as a product is obtained.
[0031]
Through these steps, as shown in FIGS. 3 and 4, it is possible to secure the stop-off region H1 in which the penetration of the brazing material 7 is prevented to a predetermined depth on the non-brazing surface side of the honeycomb seal 1. Can be. In other words, it is possible to prevent the brazing material 7 from reaching the small gap 5 only to a certain height despite the presence of the small gap 5. The hatched portion in FIG. 3 represents the height region H2 where the brazing material 7 shown in FIG. 4 has penetrated.
[0032]
As described above, since the area up to the predetermined depth on the side to be shaved is secured as the stop-off area H1, good machinability can be maintained even when brazing is performed.
When the brazing material 7 is arranged on the base material 10 using the sheet-like brazing material 7 as described above, the brazing material 7 can be uniformly supplied to the upper surface of the base material 10. As a result, the variation in brazing is reduced, and the occurrence of defects (brazing) is reduced.
[0033]
The brazing material 7 may be arranged on the base material 10 by sprinkling the powder of the brazing material 7 in FIG. 5F as in the other embodiment shown in FIG. The other steps in this embodiment are exactly the same as the other steps shown in FIGS. 1 and 2, and thus the description will be omitted.
[0034]
【The invention's effect】
According to the brazing structure of the machinable sealing material according to the first aspect of the present invention, since the brazing structure has the stop-off region, it is possible to prevent a decrease in machinability due to penetration of the brazing material. .
[0035]
According to the method for brazing a machinable seal material according to the second aspect of the present invention, a stop-off region can be ensured for the machinable seal material before brazing, so that the brazing material is permeated. It is possible to prevent a decrease in machinability.
[0036]
According to the method for brazing a machinable seal material according to claim 3, the stop-off region can be secured accurately and reliably, so that when brazing, the brazing material is transferred to the stop-off region. Can be reliably suppressed.
[0037]
Further, according to the brazing method of the machinable sealing material according to the fourth aspect, when the brazing material is arranged on the base material, it is possible to reduce the variation in the brazing.
[Brief description of the drawings]
FIG. 1 is a process explanatory view showing one embodiment of a method for brazing a machinable sealing material of the present invention.
FIG. 2 is a process explanatory view showing a partially modified example of the embodiment.
FIG. 3 is a schematic perspective view of a brazing structure for a honeycomb seal obtained by performing processing in the order of the steps in FIG. 1;
FIG. 4 is a sectional view taken along line III-III of FIG. 3;
FIG. 5 is a process explanatory view showing another embodiment of the brazing method of the machinable sealing material of the present invention.
FIG. 6 is a schematic perspective view of a conventional brazing structure for a machinable sealing material.
FIG. 7 is a sectional view taken along the line VI-VI in FIG. 6;
FIG. 8 is a process explanatory view of a conventional method for brazing a machinable sealing material.
[Explanation of symbols]
1 Honeycomb seal (Machinable seal material)
Reference Signs List 2 corrugated thin plate 3 small compartment section 4 overlapping section 5 minute gap 7 brazing material 9 heating furnace 10 base material 12 masking sheet 13 stop-off agent 13a stop-off agent film H1 stop-off region

Claims (4)

複数枚の波形薄板を重ね合わせて空所と隔壁よりなる蜂の巣状の小室区画構造を持った板状体をなし、基材側に対して固定されることで該基材及び回転体間の隙間をシールし、前記回転体が接触した場合に自らが削られる被削性シール材を、前記基材に対してろう付けする構造において、
前記被削性シール材の非ろう付け面側の所定深さまで、ろう材の浸透を阻止したストップオフ領域を設けたことを特徴とする被削性シール材のろう付け構造。A plurality of corrugated thin plates are overlapped to form a plate-like body having a honeycomb-shaped small chamber defined by voids and partition walls, and the gap between the base material and the rotating body is fixed to the base material side. In the structure of brazing a machinable sealing material that is itself cut when the rotating body comes into contact with the base material,
A brazing structure for a machinable sealing material, comprising a stop-off region for preventing penetration of the brazing material to a predetermined depth on the non-brazing surface side of the machinable sealing material. 複数枚の波形薄板を重ね合わせて空所と隔壁よりなる蜂の巣状の小室区画構造を持った板状体をなし、基材側に対して固定されることで該基材及び回転体間の隙間をシールし、前記回転体が接触した場合に自らが削られる被削性シール材を、前記基材に対してろう付けする方法において、
前記被削性シール材の一方の面をなす非ろう付け面側の所定深さまで、ろう材の浸透を阻止するストップオフ領域を確保し、その後、前記被削性シール材の他方の面を前記基材に対してろう付けすることを特徴とする被削性シール材のろう付け方法。A plurality of corrugated thin plates are overlapped to form a plate-like body having a honeycomb-shaped small chamber defined by voids and partition walls, and the gap between the base material and the rotating body is fixed to the base material side. Sealing, in the method of brazing a machinable sealing material that is cut by itself when the rotating body comes into contact with the base material,
Until a predetermined depth on the non-brazing surface side forming one surface of the machinable sealing material, a stop-off region for preventing the penetration of the brazing material is secured, and then the other surface of the machinable sealing material is A method of brazing a machinable sealing material, comprising brazing to a substrate. 請求項２に記載の被削性シール材のろう付け方法において、
前記被削性シール材のろう付け面側をマスキングシートに刺し込むことで、前記ストップオフ領域以外の領域をマスキングする工程と、
該工程後の前記被削性シール材にストップオフ剤を付着させることで、前記ストップオフ領域にストップオフ剤の膜を形成する工程と、
該工程後の前記被削性シール材から前記マスキングシートを除去する工程と、
該工程後の前記被削性シール部材のろう付け面側を前記基材に重ね合わせ、これらの間にろう材を配置する工程と、
該工程後の前記被削性シール材及び前記基材を加熱してろう付け処理する工程と、
を備えることを特徴とする被削性シール材のろう付け方法。The brazing method for a machinable sealing material according to claim 2,
By piercing the brazing surface side of the machinable sealing material into a masking sheet, a step of masking an area other than the stop-off area,
Forming a film of a stop-off agent in the stop-off region by attaching a stop-off agent to the machinable sealing material after the step;
Removing the masking sheet from the machinable sealing material after the step;
A step of superposing the brazing surface side of the machinable seal member after the step on the base material, and disposing a brazing material therebetween.
A step of heating and brazing the machinable sealing material and the base material after the step,
A brazing method for a machinable sealing material, comprising: 請求項３に記載の被削性シール材のろう付け方法において、
前記ろう材としてシート状のろう材を用い、
このシート状のろう材を、前記ろう材を配置する工程で、前記基材及び前記被削性シール部材間に挟み込んで行うことを特徴とする被削性シール材のろう付け方法。The method for brazing a machinable sealing material according to claim 3,
Using a sheet-like brazing material as the brazing material,
A brazing method for a machinable sealing material, wherein the sheet-shaped brazing material is sandwiched between the base material and the machinable sealing member in the step of disposing the brazing material.
JP2002345539A 2002-11-28 2002-11-28 Brazing method of machinable sealing material and manufacturing method of casing side base material Expired - Fee Related JP4176454B2 (en)

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DE102004025692B4 (en) * 2004-05-26 2006-05-11 Mitsubishi Heavy Industries, Ltd. Brazing construction for abradable sealing material used in turbine, includes infiltration prevention agent which is filled on non-brazing side upto specific depth so as to restrict infiltration of brazing filler metals
DE102008026941B4 (en) * 2008-06-05 2012-02-02 Mtu Aero Engines Gmbh Device for connecting a honeycomb seal with a seal carrier
JP2016513200A (en) * 2013-01-31 2016-05-12 シーメンス エナジー インコーポレイテッド Local repair of superalloy parts
KR101791976B1 (en) * 2013-01-31 2017-11-01 지멘스 에너지, 인코포레이티드 Localized repair of superalloy component
KR102097612B1 (en) * 2019-04-16 2020-04-06 하나아이티엠(주) Brazing Process using Brazing Powder Spread Device for Low Pressure Turbine Air Seal
KR102097611B1 (en) * 2019-04-16 2020-04-06 하나아이티엠(주) Brazing Powder Spread Device for Low Pressure Turbine Air Seal

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004025692B4 (en) * 2004-05-26 2006-05-11 Mitsubishi Heavy Industries, Ltd. Brazing construction for abradable sealing material used in turbine, includes infiltration prevention agent which is filled on non-brazing side upto specific depth so as to restrict infiltration of brazing filler metals
DE102008026941B4 (en) * 2008-06-05 2012-02-02 Mtu Aero Engines Gmbh Device for connecting a honeycomb seal with a seal carrier
JP2016513200A (en) * 2013-01-31 2016-05-12 シーメンス エナジー インコーポレイテッド Local repair of superalloy parts
KR101791976B1 (en) * 2013-01-31 2017-11-01 지멘스 에너지, 인코포레이티드 Localized repair of superalloy component
KR102097612B1 (en) * 2019-04-16 2020-04-06 하나아이티엠(주) Brazing Process using Brazing Powder Spread Device for Low Pressure Turbine Air Seal
KR102097611B1 (en) * 2019-04-16 2020-04-06 하나아이티엠(주) Brazing Powder Spread Device for Low Pressure Turbine Air Seal

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