JPH09136260A - Cooling hole machining method for gas turbine blade - Google Patents
Cooling hole machining method for gas turbine bladeInfo
- Publication number
- JPH09136260A JPH09136260A JP29666595A JP29666595A JPH09136260A JP H09136260 A JPH09136260 A JP H09136260A JP 29666595 A JP29666595 A JP 29666595A JP 29666595 A JP29666595 A JP 29666595A JP H09136260 A JPH09136260 A JP H09136260A
- Authority
- JP
- Japan
- Prior art keywords
- cooling hole
- ceramic coating
- coating layer
- gas turbine
- cooling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/06—Cooling passages of turbine components, e.g. unblocking or preventing blocking of cooling passages of turbine components
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、冷却用貫通孔を有
しセラミックコーティングされたガスタービン翼の冷却
孔加工方法に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for processing cooling holes in a gas turbine blade having a through hole for cooling and having a ceramic coating.
【０００２】[0002]
【従来の技術】ガスタービン翼は、主にＮｉ基耐熱合金
により形成され、翼部には冷却空気を流すための多数の
冷却孔があり、表面には耐熱性向上のためにＺｒＯ2 等
のセラミックコーティングが行なわれている。2. Description of the Related Art A gas turbine blade is mainly formed of a Ni-base heat-resistant alloy, has a large number of cooling holes for flowing cooling air in the blade portion, and has a surface made of ZrO 2 or the like for improving heat resistance. Ceramic coating is applied.
【０００３】従来の冷却孔の加工方法においては、コー
ティング前にあらかじめ孔を設けた状態でセラミックコ
ーティングする方法か、あるいはセラミックコーティン
グの上から貫通孔を加工する方法が用いられていた。In the conventional method of processing cooling holes, there has been used a method of ceramic coating in the state where holes are provided in advance before coating, or a method of processing through holes on the ceramic coating.
【０００４】[0004]
【発明が解決しようとする課題】従来のガスタービン翼
の冷却孔加工方法においては、前述のとおり２種類の方
法があった。As described above, there are two types of conventional methods for processing cooling holes in gas turbine blades.
【０００５】セラミックコーティング前に冷却孔をあけ
ておく方法においては、放電加工で冷却孔をあけた後
に、溶射もしくは物理蒸着（ＰＶＤ）によりボンドコー
ト材（ＭＣｒＡｌＹ：Ｍは金属であり、ＣｏやＮｉがよ
く使われる）とセラミックスをコーティングしていた。In the method of forming cooling holes before ceramic coating, after the cooling holes are formed by electric discharge machining, the bond coat material (MCrAlY: M is a metal, Co or Ni is formed by thermal spraying or physical vapor deposition (PVD). Is often used) and ceramics were coated.
【０００６】この方法では、溶射あるいはＰＶＤ中に冷
却孔が閉塞するという課題があった。この閉塞を防止す
るためには各冷却孔ごとのマスキングをすればよいが、
多数の冷却孔をそれぞれ正確にマスキングするのは手間
がかヽり、技術的にも課題があった。This method has a problem that the cooling holes are closed during the thermal spraying or PVD. In order to prevent this blockage, masking of each cooling hole may be performed, but
Accurate masking of each of the numerous cooling holes is time-consuming and technically problematic.
【０００７】一方、セラミックコーティング後にレーザ
ー光でセラミックス層、ボンド層及び母材を一気に局部
溶融させて貫通孔を設ける方法においては、母材に用い
られるＮｉ基耐熱合金は、強度確保のかめにＴｉやＡｌ
を添加しており、ＴｉやＡｌはＮｉの融点を下げるた
め、レーザー光で冷却孔をあけた場合、多量の熱で母材
を溶融して冷却孔の周囲に０．１mm程度の深さの割れを
生じさせるという課題があった。On the other hand, in the method of locally melting the ceramic layer, the bond layer and the base material at once by laser light after the ceramic coating to form the through holes, the Ni-base heat-resistant alloy used for the base material is Ti for securing strength. And Al
Since Ti and Al lower the melting point of Ni, when a cooling hole is opened with laser light, the base material is melted by a large amount of heat and a depth of about 0.1 mm is formed around the cooling hole. There was a problem of causing cracks.
【０００８】本発明は、上記課題を解決し、加工が容易
で、セラミックコーティング後に孔明加工を行い、母材
に割れを生じることのない加工方法を実現しようとする
ものである。The present invention is intended to solve the above problems and to realize a processing method which is easy to process and which does not cause cracks in a base material by performing a perforating process after ceramic coating.
【０００９】[0009]
【課題を解決するための手段】請求項１に記載の発明に
係るガスタービン翼の冷却孔加工方法は、ガスタービン
翼の冷却孔が設けられる部分のセラミックコーティング
層をショットブラストにより除去した後、セラミックコ
ーティング層が除去された部分のボンドコート層及び翼
母材に放電加工により貫通孔を形成して冷却孔とするこ
とを特徴としている。According to a first aspect of the present invention, there is provided a gas turbine blade cooling hole machining method, wherein a ceramic coating layer of a portion of a gas turbine blade where cooling holes are provided is removed by shot blasting, It is characterized in that a through hole is formed in the bond coat layer and the blade base material in the portion where the ceramic coating layer is removed by electric discharge machining to form a cooling hole.
【００１０】上記において、ガスタービン翼の冷却孔が
設けられる部分にショットブラストを行ってセラミック
コーティング層を除去すると、その内部に設けられたボ
ンドコート層あるいは翼母材が露出する。In the above, when the ceramic coating layer is removed by shot blasting the portion where the cooling holes of the gas turbine blade are provided, the bond coat layer or blade base material provided inside is exposed.
【００１１】このボンドコート層及び翼母材は通電性を
有するため、セラミックコーティング層が除去された部
分に電極を挿入して放電させることができ、放電加工に
より冷却孔となる貫通孔を形成することができる。Since the bond coat layer and the blade base material have electrical conductivity, an electrode can be inserted into the portion where the ceramic coating layer has been removed to cause an electric discharge, and a through hole serving as a cooling hole is formed by electric discharge machining. be able to.
【００１２】上記放電加工は、レーザー加工のように母
材を多量の熱で溶融するものではないため、冷却孔の周
辺に割れを生じることなく、良好な冷却孔を加工するこ
とが可能となる。Unlike the laser machining, the above-mentioned electric discharge machining does not melt the base material with a large amount of heat, so that a good cooling hole can be machined without causing cracks around the cooling hole. .
【００１３】[0013]
【発明の実施の形態】本発明の実施の一形態に係るガス
タービン翼の冷却孔加工方法について、図１乃至図３に
より説明する。BEST MODE FOR CARRYING OUT THE INVENTION A method for processing a cooling hole of a gas turbine blade according to an embodiment of the present invention will be described with reference to FIGS.
【００１４】図１乃至図３に示す本実施形態の冷却孔加
工方法においては、図３に示すようにＮｉ基耐熱合金製
の翼母材１にボンドコートとしてＭＣｒＡｌＹ合金がコ
ーティングされてボンドコート層２が形成され、その上
にセラミックがコーティングされてセラミックコーティ
ング層３が形成されたガスタービン翼について、以下の
手順で冷却孔の加工が行なわれる。In the cooling hole machining method of the present embodiment shown in FIGS. 1 to 3, as shown in FIG. 3, a blade base material 1 made of a Ni-base heat-resistant alloy is coated with MCrAlY alloy as a bond coat to form a bond coat layer. With respect to the gas turbine blade on which No. 2 is formed and the ceramic coating layer 3 is formed by coating the ceramic on the No. 2, cooling holes are processed in the following procedure.
【００１５】即ち、まず、図１（ａ）に示すように冷却
孔に対応した穴を有する穴あき当て板４を翼表面にはり
つける。次に、図１（ｂ）に示すように当て板４はりつ
けた状態でアルミナ（Ａｌ2 Ｏ3 ）粉末５を用いてショ
ットブラストを行い、ガスタービン翼の冷却孔が設けら
れる部分のセラミックスを除去する。That is, first, as shown in FIG. 1A, a perforated plate 4 having holes corresponding to cooling holes is attached to the blade surface. Next, as shown in FIG. 1B, shot blasting is performed using alumina (Al 2 O 3 ) powder 5 in a state where the contact plate 4 is attached to remove the ceramics in the portion where the cooling holes of the gas turbine blade are provided. To do.
【００１６】冷却孔が設けられる部分のセラミックスの
除去が完了すると、当て板５をはずして図１（ｃ）に示
す状態とした後、これを水中に浸漬し、図１（ｄ）に示
すように放電加工用電極６をセラミックコーティング層
３の除去部に挿入し、放電加工を行い、図１（ｅ）に示
すようにボンドコート層２及び翼母材１を貫通して冷却
孔の加工を完了する。When the removal of the ceramic in the portion where the cooling holes are provided is completed, the backing plate 5 is removed to obtain the state shown in FIG. 1 (c), which is then immersed in water, as shown in FIG. 1 (d). Then, the electric discharge machining electrode 6 is inserted into the removed portion of the ceramic coating layer 3, electric discharge machining is performed, and as shown in FIG. 1 (e), the bond coat layer 2 and the blade base material 1 are penetrated to form a cooling hole. Complete.
【００１７】Ａｌ2 Ｏ3 粉末のショットブラストにより
セラミックコーティング層３が除去された冷却孔が加工
される部分については、上記の放電加工を順次行い、図
２に示すように冷却孔の加工が行われたガスタービン翼
を得ている 上記において、冷却孔に対応する多数の穴が設けられた
当て板４をガスタービン翼にはり付け、Ａｌ2 Ｏ3 粉末
５を用いてショットブラストを行うと、ガスタービン翼
の冷却孔が設けられる部分のセラミックコーティング層
３が除去され、通電性を有するＭＣｒＡｌＹボンドコー
ト層２あるいは翼母材１が露出する。For the portion where the cooling hole from which the ceramic coating layer 3 has been removed by the shot blasting of Al 2 O 3 powder is to be processed, the above-mentioned electric discharge machining is sequentially performed, and the cooling hole is processed as shown in FIG. In the above, when the backing plate 4 provided with a large number of holes corresponding to the cooling holes is attached to the gas turbine blade and shot blasting is performed using the Al 2 O 3 powder 5, The ceramic coating layer 3 in the portion where the cooling holes of the gas turbine blade are provided is removed, and the MCrAlY bond coat layer 2 or blade base material 1 having electrical conductivity is exposed.
【００１８】そのため、これを水中に浸漬し、セラミッ
クコーティング層３が除去された部分に電極６を挿入し
て放電加工を行うことが可能となり、この放電加工によ
り冷却孔を形成することが可能となる。Therefore, it becomes possible to immerse this in water and insert the electrode 6 into the portion where the ceramic coating layer 3 has been removed to perform electrical discharge machining, and it is possible to form cooling holes by this electrical discharge machining. Become.
【００１９】上記放電加工は、レーザー加工のように翼
母材１を多量の熱で溶融するものではないため、冷却孔
の周辺に割れを生じることなく、冷却孔を加工すること
ができるようになった。Unlike the laser machining, the above-mentioned electric discharge machining does not melt the blade base material 1 with a large amount of heat, so that the cooling holes can be machined without causing cracks around the cooling holes. became.
【００２０】上記セラミックコーティング層３の除去に
ついては、粒径１００〜３００μｍのＡｌ2 Ｏ3 粉末５
を用い、ショットブラストの空気圧を５〜１０Kgf/cm2
の圧力とし、ブラストノズル先端と製品表面間のショッ
トブラスト距離を５０〜１５０mmとしてショットブラス
トを行ったところ、約１mmφの範囲でセラミックコーテ
ィング層３を除去することができた。For removing the ceramic coating layer 3, Al 2 O 3 powder 5 having a particle size of 100 to 300 μm is used.
With a shot blasting air pressure of 5-10 Kgf / cm 2
When the shot blasting was carried out under the pressure of, and the shot blasting distance between the tip of the blasting nozzle and the product surface was 50 to 150 mm, the ceramic coating layer 3 could be removed within a range of about 1 mmφ.
【００２１】また、放電加工については、直径０．５〜
０．７mmの銅製の管状電極６を用い、加工電流は約８
Ａ、放電維持電圧は約２０Ｖとし、管内より加工液を噴
射しながら複数本（２０本）同時加工を行ったところ、
直径０．５〜１．０mm、長さ３０mm以下の穴に対し、穴
の精度は直径で±０．１mm程度、電極消耗は１０％以内
であり、良好な冷却孔を加工することができた。For electric discharge machining, the diameter is 0.5 to
0.7mm copper tubular electrode 6 is used and processing current is about 8
A, the discharge sustaining voltage was about 20 V, and when a plurality of (20) were simultaneously machined while injecting the machining fluid from the inside of the pipe,
For holes with a diameter of 0.5 to 1.0 mm and a length of 30 mm or less, the accuracy of the holes was about ± 0.1 mm in diameter and the electrode consumption was within 10%, and good cooling holes could be processed. .
【００２２】[0022]
【発明の効果】本発明のガスタービン翼の冷却孔加工方
法においては、冷却孔が設けられる部分のセラミックコ
ーティング層をショットブラストにより除去した後、こ
の部分の露出したボンドコート層及び翼母材に放電加工
を施し冷却孔となる貫通孔を形成するものとしたことに
よって、従来のレーザー加工による場合に冷却孔の周辺
の翼母材に生じていた割れが発生せず、健全で精度のよ
い冷却孔を容易に得ることが可能となる。In the gas turbine blade cooling hole processing method of the present invention, after removing the ceramic coating layer in the portion where the cooling hole is provided by shot blasting, the exposed bond coat layer and blade base material in this portion are removed. By performing electrical discharge machining to form through holes that serve as cooling holes, the blade base metal around the cooling holes does not crack when using conventional laser processing, and sound cooling is performed with good accuracy. The holes can be easily obtained.
【図１】本発明の実施の一形態に係るガスタービン翼の
冷却孔加工方法の説明図で、（ａ）は翼に当て板をはり
つけた状態の斜視図、（ｂ）はセラミックコーティング
層除去中の断面図、（ｃ）はセラミックコーティング層
除去後の断面図、（ｄ）は冷却孔放電加工中の断面図、
（ｅ）は冷却孔の貫通を完了した状態の断面図である。FIG. 1 is an explanatory view of a method for processing a cooling hole of a gas turbine blade according to an embodiment of the present invention, (a) is a perspective view of a blade with a backing plate attached, and (b) is a ceramic coating layer removed layer. A sectional view inside, (c) a sectional view after removing the ceramic coating layer, (d) a sectional view during cooling hole electric discharge machining,
(E) is a cross-sectional view of a state in which the penetration of the cooling hole is completed.
【図２】上記一実施形態に係る冷却孔加工後のガスター
ビン翼の説明図で、（ａ）は斜視図、（ｂ）は（ａ）の
Ａ−Ａ矢視図である。2A and 2B are explanatory views of a gas turbine blade after cooling holes are processed according to the above embodiment, FIG. 2A is a perspective view, and FIG. 2B is a view taken along the line AA of FIG.
【図３】上記一実施形態に係る冷却孔加工前のガスター
ビン翼の説明図で、（ａ）は斜視図、（ｂ）は（ａ）の
Ｂ−Ｂ矢視図である。3A and 3B are explanatory views of a gas turbine blade before cooling hole processing according to the above embodiment, FIG. 3A is a perspective view, and FIG. 3B is a view taken along the line BB of FIG.
１ 翼母材 ２ ＭＣｒＡｌＹボンドコート層 ３ セラミックコーティング層 ４ 穴あき当て板 ５ Ａｌ2 Ｏ3 粉末 ６ 放電加工用電極1 blade base material 2 MCrAlY bond coat layer 3 ceramic coating layer 4 perforated plate 5 Al 2 O 3 powder 6 electrode for electric discharge machining
Claims (1)
分のセラミックコーティング層をショットブラストによ
り除去した後、セラミックコーティング層が除去された
部分のボンドコート層及び翼母材に放電加工により貫通
孔を形成して冷却孔とすることを特徴とするガスタービ
ン翼の冷却孔加工方法。1. After removing a ceramic coating layer of a portion where a cooling hole of a gas turbine blade is provided by shot blasting, a through hole is formed in the bond coat layer and the blade base material of the portion where the ceramic coating layer is removed by electric discharge machining. A method of forming a cooling hole for a gas turbine blade, comprising forming the cooling hole to form a cooling hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP29666595A JPH09136260A (en) | 1995-11-15 | 1995-11-15 | Cooling hole machining method for gas turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP29666595A JPH09136260A (en) | 1995-11-15 | 1995-11-15 | Cooling hole machining method for gas turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH09136260A true JPH09136260A (en) | 1997-05-27 |
Family
ID=17836498
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP29666595A Withdrawn JPH09136260A (en) | 1995-11-15 | 1995-11-15 | Cooling hole machining method for gas turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH09136260A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6495197B1 (en) * | 1999-04-28 | 2002-12-17 | Aerospatiale Matra Airbus | Method for providing metallized areas on surface by electrically detecting removal of insulating layer |
| JP2007519530A (en) * | 2003-12-15 | 2007-07-19 | ターボコンバスター・テクノロジー・インコーポレーテッド | Method for removing a thermal barrier coating |
| WO2007134916A1 (en) * | 2006-05-19 | 2007-11-29 | Siemens Aktiengesellschaft | Method for preparing a component consisting of an electroconductive base material in order to carry out an erosive process |
| JP2011106448A (en) * | 2009-11-16 | 2011-06-02 | Siemens Ag | Coating method for component with partially closed holes and method for opening the coated hole |
| EP2439377A2 (en) | 2010-10-07 | 2012-04-11 | Hitachi, Ltd. | Method of working a cooling hole of a turbine blade |
| JP2012072705A (en) * | 2010-09-29 | 2012-04-12 | Hitachi Ltd | Method for manufacturing gas turbine blade |
| JP2012132451A (en) * | 2010-12-23 | 2012-07-12 | General Electric Co <Ge> | Method for modifying substrate for forming passage hole in the substrate, and article relating thereto |
| WO2015073845A1 (en) * | 2013-11-15 | 2015-05-21 | United Technologies Corporation | Fluidic machining method and system |
| KR101533784B1 (en) * | 2014-02-27 | 2015-07-03 | 데크컴퍼지트 주식회사 | Method for anti-oxidation coating aircraft brake disc |
| US20160281511A1 (en) * | 2012-11-16 | 2016-09-29 | Siemens Aktiengesellschaft | Modified surface around a hole |
-
1995
- 1995-11-15 JP JP29666595A patent/JPH09136260A/en not_active Withdrawn
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6495197B1 (en) * | 1999-04-28 | 2002-12-17 | Aerospatiale Matra Airbus | Method for providing metallized areas on surface by electrically detecting removal of insulating layer |
| JP2007519530A (en) * | 2003-12-15 | 2007-07-19 | ターボコンバスター・テクノロジー・インコーポレーテッド | Method for removing a thermal barrier coating |
| WO2007134916A1 (en) * | 2006-05-19 | 2007-11-29 | Siemens Aktiengesellschaft | Method for preparing a component consisting of an electroconductive base material in order to carry out an erosive process |
| WO2007134620A1 (en) * | 2006-05-19 | 2007-11-29 | Siemens Aktiengesellschaft | Method for preparing a component consisting of an electroconductive base material in order to carry out an erosive process |
| JP2011106448A (en) * | 2009-11-16 | 2011-06-02 | Siemens Ag | Coating method for component with partially closed holes and method for opening the coated hole |
| US8980372B2 (en) | 2009-11-16 | 2015-03-17 | Siemens Aktiengesellschaft | Process for coating a component having partially closed holes and process for opening the holes |
| JP2012072705A (en) * | 2010-09-29 | 2012-04-12 | Hitachi Ltd | Method for manufacturing gas turbine blade |
| EP2439377A2 (en) | 2010-10-07 | 2012-04-11 | Hitachi, Ltd. | Method of working a cooling hole of a turbine blade |
| JP2012132451A (en) * | 2010-12-23 | 2012-07-12 | General Electric Co <Ge> | Method for modifying substrate for forming passage hole in the substrate, and article relating thereto |
| US20160281511A1 (en) * | 2012-11-16 | 2016-09-29 | Siemens Aktiengesellschaft | Modified surface around a hole |
| WO2015073845A1 (en) * | 2013-11-15 | 2015-05-21 | United Technologies Corporation | Fluidic machining method and system |
| US10107110B2 (en) | 2013-11-15 | 2018-10-23 | United Technologies Corporation | Fluidic machining method and system |
| US10954800B2 (en) | 2013-11-15 | 2021-03-23 | Raytheon Technologies Corporation | Fluidic machining method and system |
| KR101533784B1 (en) * | 2014-02-27 | 2015-07-03 | 데크컴퍼지트 주식회사 | Method for anti-oxidation coating aircraft brake disc |
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