JPH07233946A - Heat resistance and anticorrosion treated combustor nozzle for gas turbine - Google Patents
Heat resistance and anticorrosion treated combustor nozzle for gas turbineInfo
- Publication number
- JPH07233946A JPH07233946A JP2512194A JP2512194A JPH07233946A JP H07233946 A JPH07233946 A JP H07233946A JP 2512194 A JP2512194 A JP 2512194A JP 2512194 A JP2512194 A JP 2512194A JP H07233946 A JPH07233946 A JP H07233946A
- Authority
- JP
- Japan
- Prior art keywords
- nozzle
- plating
- portions
- treatment
- masking
- 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.)
- Granted
Links
Landscapes
- Coating By Spraying Or Casting (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明はガスタービンの燃焼器に
適用されるノズルに関するもので、ボイラー等のバーナ
部品にも適用できるものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a nozzle applied to a combustor of a gas turbine, and can also be applied to burner parts such as boilers.
【０００２】[0002]
【従来の技術】従来のガスタービン用燃焼器におけるノ
ズル構造は図５の如くなっており、油燃料やガス燃料を
通す燃料ノズル穴２がノズル本体１内に設けられ、ノズ
ル内で分散しながら燃料を噴霧するようになっている。
一方燃焼用空気も燃料ノズル穴２より外周側であるが、
ノズル本体１内を通る空気ノズル穴３を経由し、ノズル
先端より噴き出すようになっている。2. Description of the Related Art A conventional nozzle structure in a gas turbine combustor is as shown in FIG. 5, in which a fuel nozzle hole 2 for passing oil fuel or gas fuel is provided in a nozzle body 1 and is dispersed in the nozzle. It is designed to spray fuel.
On the other hand, the combustion air is also on the outer peripheral side of the fuel nozzle hole 2,
The air is ejected from the tip of the nozzle through the air nozzle hole 3 that passes through the inside of the nozzle body 1.
【０００３】[0003]
【発明が解決しようとする課題】このような従来のノズ
ルにおいては、燃料ノズル穴２及び空気ノズル穴３の先
端噴き出し部に囲まれた中央部分は燃焼ガスがよどみや
すく、この為未燃成分（炭素分、他）が付着したり、高
温の火炎の熱を受けて高温化する傾向にある。この結
果、ノズル先端の中央部分では高温酸化や高温腐食によ
る損傷を発生しノズル全体の耐久性を著しく低下させる
ケースがしばしばみられる。このため、ノズルを耐熱性
に優れた材質に変更したり、ノズル全体を耐熱表面処理
することが試みられたが、何れもコストの上昇を招き、
また前記材質の変更による耐熱性を向上させようとする
と、材料自体が硬化する傾向にあり、ノズルの加工性が
悪化する等の諸問題を生じた。そこで、本発明はこのよ
うな従来のノズルにおける諸課題を解決して、耐熱、耐
食性に優れ、ノズル中央部の損傷が軽減できる低コスト
で長寿命のガスタービン用燃焼器ノズルを提供せんとす
るものである。In such a conventional nozzle, the combustion gas is apt to stagnate in the central portion surrounded by the tip ejection portions of the fuel nozzle hole 2 and the air nozzle hole 3, so that unburned components ( Carbon content, etc.) is attached, and tends to heat up due to the heat of a high-temperature flame. As a result, the center of the nozzle tip is often damaged by high temperature oxidation and high temperature corrosion, and the durability of the entire nozzle is often significantly reduced. For this reason, it has been attempted to change the nozzle to a material having excellent heat resistance, or to perform heat resistant surface treatment of the entire nozzle, but both of them cause an increase in cost,
Further, when trying to improve the heat resistance by changing the material, the material itself tends to be hardened, which causes various problems such as deterioration of the workability of the nozzle. Therefore, the present invention solves various problems in such a conventional nozzle, and provides a low-cost and long-life combustor nozzle for a gas turbine, which is excellent in heat resistance and corrosion resistance and can reduce damage to the central portion of the nozzle. It is a thing.
【０００４】[0004]
【課題を解決するための手段】このため本発明は、ノズ
ル先端の受熱部分のみをメッキ、溶射、Ａｌ−Ｓｉ、或
いはセラミックスラリーコーティング等で比較的熱影響
の少ない手法で表面処理を施し、ノズル自体の耐熱、耐
食性を向上させてなるもので、これを課題解決のための
手段とするものである。Therefore, according to the present invention, only the heat receiving portion at the tip of the nozzle is subjected to surface treatment by a method having a relatively small thermal influence by plating, thermal spraying, Al-Si, or ceramic slurry coating, and the nozzle is It has improved heat resistance and corrosion resistance, and is used as a means for solving the problems.
【０００５】[0005]
【作用】本発明は、ノズル本体を従来材料（ＳＵＳ３０
４等）及び工法で製作した後、ノズル先端の燃焼ガスの
よどみ部に相当する部分のみをメッキすべく、同メッキ
部分以外にマスキングを施し、所定のメッキ液にノズル
先端部分を浸し、膜厚５μｍ程度のアモルファスクロム
メッキを形成させたことにより、ノズル本体が従来材料
と工法であるため、基本的にノズル製作工法等を変更せ
ずに、ノズル先端部のみを処理する工程を追加すればよ
いので、処理コストの低減化を実現化し、耐熱、耐食性
に優れた長寿命のガスタービン用燃焼ノズルを提供でき
る。また本発明では、ノズル先端の表面処理方法として
メッキ以外に、Ｎｉ−Ｃｒ合金のプラズマ溶射やＡｌ−
Ｓｉスラリーコーティング、或いはセラミックコーティ
ング等によるものがある。In the present invention, the nozzle body is made of the conventional material (SUS30).
4 etc.) and the manufacturing method, to mask only the portion corresponding to the stagnation part of the combustion gas at the nozzle tip, mask the area other than the plated portion, immerse the nozzle tip portion in the prescribed plating solution, and film thickness Since the nozzle body is made of the conventional material and method by forming the amorphous chrome plating of about 5 μm, it is basically necessary to add the step of treating only the nozzle tip without changing the nozzle manufacturing method or the like. Therefore, it is possible to realize a reduction in processing cost, and to provide a long-life gas turbine combustion nozzle that is excellent in heat resistance and corrosion resistance. Further, in the present invention, as the surface treatment method of the nozzle tip, in addition to plating, plasma spraying of Ni-Cr alloy or Al-
There are those by Si slurry coating or ceramic coating.
【０００６】[0006]
【実施例】以下本発明の実施例を図面に基づいて説明す
る。 〈具体例１（メッキ）〉従来法で製作したＳＵＳ３０４
製等のノズル本体１に図１に示すようにメッキ処理を施
す部分以外の部分にマスキング１０を行った後、メッキ
液２０に浸し、表１のような条件で膜厚５μｍ程度を目
標にアモルファスクロムメッキを行った。Embodiments of the present invention will be described below with reference to the drawings. <Specific example 1 (plating)> SUS304 manufactured by a conventional method
As shown in FIG. 1, masking 10 is applied to a portion of the nozzle body 1 made of a product or the like other than the portion to be plated, and then immersed in a plating solution 20 and amorphous under the conditions as shown in Table 1 with a target film thickness of about 5 μm. It was chrome plated.
【表１】 [Table 1]
【０００７】〈具体例２（溶射）〉具体例１と同様に、
従来型ノズル本体１を図２に示すように表面処理すべき
部分以外の部分に耐熱テープでマスキング１０を行った
後、溶射材の定着化促進のために溶射面をグリッドブラ
ストにて粗面化し、その後５０Ｎｉ−５Ｃｒ合金を膜厚
１００μｍ程度の目標にプラズマ溶射３０を行い、ノズ
ル先端表面にＮｉ−Ｃｒ合金４０の層を形成して製品と
した。<Specific Example 2 (Spraying)> As in Specific Example 1,
As shown in FIG. 2, the conventional nozzle body 1 is masked with a heat-resistant tape on a portion other than the portion to be surface-treated, and then the sprayed surface is roughened by grid blasting to promote fixation of the sprayed material. After that, plasma spraying 30 was performed on a target of 50 Ni-5Cr alloy with a film thickness of about 100 μm, and a layer of Ni—Cr alloy 40 was formed on the nozzle tip surface to obtain a product.
【０００８】〈具体例３（Ａｌ−Ｓｉスラリーコーティ
ング）〉前記第１具体例と同様、従来型ノズル本体１に
対し図３に示すようなコーティング処理部以外の部分に
マスキング１０を通常の粘着テープ等で行った後、Ａ
ｌ、Ｓｉ化合物を有機性溶媒に分散させたスラリー５０
を被処理面へハケ等を利用して塗布し、１２０℃程度に
保った乾燥器中に２時間挿入して一次乾燥を行った。次
にマスキングテープを取り除き３５０〜４００℃で２時
間の二次乾燥を行った後、３％Ｈ2 −Ｎ2 ガス雰囲気中
で８５０℃、３時間の熱処理６０を行った。熱処置後の
ノズルはスラリー塗布面をガラスビーズにてプラスト７
０を行い、スラリーの残渣を除去してＡｌ−Ｓｉ拡散層
８０を形成し、製品とした。なお、Ａｌ−Ｓｉスラリー
コーティングに代えてセラミックスラリーコーティング
により処理してもよい。<Specific Example 3 (Al-Si Slurry Coating)> Similar to the first specific example, the conventional nozzle body 1 is provided with a masking 10 on a portion other than the coating treatment portion as shown in FIG. Etc., then A
1, a slurry 50 in which a Si compound is dispersed in an organic solvent
Was applied to the surface to be treated using a brush or the like, and was inserted into a dryer kept at about 120 ° C. for 2 hours for primary drying. Next, the masking tape was removed, secondary drying was performed at 350 to 400 ° C. for 2 hours, and then heat treatment 60 was performed at 850 ° C. for 3 hours in a 3% H 2 —N 2 gas atmosphere. After the heat treatment, the nozzles are coated with glass beads on the slurry application surface.
0 was performed, the residue of the slurry was removed, and the Al-Si diffusion layer 80 was formed to obtain a product. Note that ceramic slurry coating may be used instead of Al-Si slurry coating.
【０００９】以上の具体例によるノズル先端部の各表面
処理によってノズル先端部へノズル本体のＳＵＳ３０４
等材料の耐熱、耐食性に優れた材料を表面処理すること
により、先端部の高温酸化及び高温腐食による腐食速度
を著しく低下させ、ノズル全体の寿命を延ばすことがで
きた。従来のものでは約１年で交換していたが、クロム
メッキしたもので約２年、溶射、Ａｌ−Ｓｉスラリーで
処理したもので約３年に延長することができた。またノ
ズル先端の必要部分のみへの処理のため、表面処理によ
る燃料ノズル穴や空気ノズル穴の変形や閉塞を防ぐこと
ができ、処理コストも全体処理に比べてほぼ１／２〜１
／３に低減できた。しかも基本的なノズル材料、構造は
従来通りである為、ノズル製作工法等の変更が不要とな
り、更に表面処理法は何れも被処理材への熱影響を比較
的低くできる為、表面処理による歪の発生等を抑制する
ことができた。SUS304 of the nozzle body is attached to the nozzle tip by each surface treatment of the nozzle tip according to the above specific example.
By surface-treating such a material having excellent heat resistance and corrosion resistance, the corrosion rate due to high temperature oxidation and high temperature corrosion of the tip portion was remarkably reduced, and the life of the entire nozzle could be extended. The conventional one had been replaced in about one year, but it could be extended to about two years with a chrome-plated one and about three years with a sprayed or Al-Si slurry treated one. In addition, since the processing is performed only on the required part of the nozzle tip, it is possible to prevent the deformation and blockage of the fuel nozzle hole and the air nozzle hole due to the surface treatment, and the processing cost is about 1/2 to 1 as compared with the whole processing.
It could be reduced to / 3. Moreover, since the basic nozzle material and structure are the same as before, there is no need to change the nozzle manufacturing method, etc. In addition, the surface treatment methods can alleviate the thermal effect on the material to be treated, so that distortion due to surface treatment It was possible to suppress the occurrence of
【００１０】図４に前記本発明の各具体例による表面処
理部分の高温酸化試験結果を示した。ノズルの使用最高
温度である大気中９００℃、１０００時間試験におい
て、従来材料ＳＵＳ３０４等に対し本発明品の酸化量は
約１／１０から１／５程度であり、優れた耐酸化性を示
した。さらに前記結果を基に、ＬＰＧ等ガス燃焼を行っ
ている実機ガスタービンのノズル部に適用し、プラント
の定期検査期間である１年間（約７５００時間）の試用
を行ったところ、従来品（ＳＵＳ３０４等の無処理品）
のノズル先端部では、肉盛補修或いは交換が必要な０．
１〜０．２mmの減肉を生じていたのに対し、本発明の具
体例１〜３ではいずれも減肉の兆候はなく健全な状態を
保っていた。FIG. 4 shows the results of the high temperature oxidation test of the surface-treated portion according to each embodiment of the present invention. In a test at a temperature of 900 ° C. in the atmosphere, which is the maximum temperature of the nozzle, for 1000 hours, the oxidation amount of the product of the present invention was about 1/10 to 1/5 of that of the conventional material SUS304 and the like, showing excellent oxidation resistance. . Furthermore, based on the above results, when applied to the nozzle part of an actual gas turbine that is performing gas combustion such as LPG, a trial was performed for one year (about 7500 hours), which is a periodic inspection period of the plant, and a conventional product (SUS304) Etc.)
No. 0, which requires overlay repair or replacement, at the nozzle tip.
While the metal loss of 1 to 0.2 mm was generated, in all of the specific examples 1 to 3 of the present invention, there was no sign of metal loss and the healthy state was maintained.
【００１１】[0011]
【発明の効果】以上詳細に説明した如く本発明によれ
ば、ガスタービン用燃焼器ノズルにおいて、メッキ、溶
射、Ａｌ−Ｓｉ、或いはセラミックスラリーコーティン
グ等の比較的熱影響の少ない表面処理法により、ノズル
先端の受熱部分のみを局部的に表面処理し、ノズル自体
の耐熱、耐久性を増加させることにより、耐熱性に優
れ、ノズル中央部の損傷を飛躍的に軽減でき、しかもノ
ズル先端の受熱部のみを局部的に表面処理すればよいの
で、低コストにて長寿命のガスタービン用燃焼ノズルを
提供できるものである。As described in detail above, according to the present invention, in a gas turbine combustor nozzle, a surface treatment method such as plating, thermal spraying, Al-Si, or ceramic slurry coating, which has a relatively small thermal effect, can be performed. By heat-treating only the heat-receiving part of the nozzle tip locally and increasing the heat resistance and durability of the nozzle itself, it has excellent heat resistance and can dramatically reduce damage to the central part of the nozzle. Since only the surface treatment is required locally, it is possible to provide a low-cost, long-life combustion turbine combustion nozzle.
【図１】本発明の第１実施例に係るメッキ法によるノズ
ルの作製図である。FIG. 1 is a manufacturing diagram of a nozzle by a plating method according to a first embodiment of the present invention.
【図２】本発明の第２実施例に係る溶射法によるノズル
の作製図である。FIG. 2 is a manufacturing diagram of a nozzle by a thermal spraying method according to a second embodiment of the present invention.
【図３】本発明の第３実施例に係るＡｌ−Ｓｉスラリー
コーティングによるノズルの作製図である。FIG. 3 is a manufacturing diagram of a nozzle formed by Al-Si slurry coating according to a third embodiment of the present invention.
【図４】本発明の高温酸化試験結果を示す説明図であ
る。FIG. 4 is an explanatory diagram showing the results of a high temperature oxidation test of the present invention.
【図５】従来のガスタービン燃焼器ノズルを示す断面図
である。FIG. 5 is a cross-sectional view showing a conventional gas turbine combustor nozzle.
１ ノズル本体 １０ マスキング ２０ メッキ液 ３０ プラズマ溶射 ４０ Ｎｉ−Ｃｒ合金 ５０ Ａｌ−Ｓｉスラリー ６０ 熱処理 ７０ ガラスビーズブラスト ８０ Ａｌ−Ｓｉ拡散層 1 Nozzle Main Body 10 Masking 20 Plating Liquid 30 Plasma Spraying 40 Ni-Cr Alloy 50 Al-Si Slurry 60 Heat Treatment 70 Glass Bead Blast 80 Al-Si Diffusion Layer
Claims (1)
ミックスラリーコーティング等の比較的熱影響の少ない
表面処理法により、ノズル先端の受熱部分のみを局部的
に表面処理し、ノズル自体の耐熱、耐久性を増加させる
ようにしたことを特徴とするガスタービン用燃焼器ノズ
ル。1. The nozzle is heat-resistant and durable by locally surface-treating only the heat-receiving portion of the nozzle tip by a surface treatment method such as plating, thermal spraying, Al-Si, or ceramic slurry coating, which has a relatively small thermal effect. A combustor nozzle for a gas turbine, characterized in that
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP06025121A JP3082823B2 (en) | 1994-02-23 | 1994-02-23 | Gas turbine combustor nozzle with heat and corrosion resistance treatment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP06025121A JP3082823B2 (en) | 1994-02-23 | 1994-02-23 | Gas turbine combustor nozzle with heat and corrosion resistance treatment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH07233946A true JPH07233946A (en) | 1995-09-05 |
| JP3082823B2 JP3082823B2 (en) | 2000-08-28 |
Family
ID=12157112
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP06025121A Expired - Lifetime JP3082823B2 (en) | 1994-02-23 | 1994-02-23 | Gas turbine combustor nozzle with heat and corrosion resistance treatment |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3082823B2 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009047414A (en) * | 2007-08-21 | 2009-03-05 | General Electric Co <Ge> | Fuel nozzle and diffusion tip for the fuel nozzle |
| JP2012149878A (en) * | 2011-01-18 | 2012-08-09 | General Electric Co <Ge> | Gas turbine combustor end cover assembly equipped with integrated flow throttle and manifold sealing |
| JP2013178035A (en) * | 2012-02-28 | 2013-09-09 | Mitsubishi Heavy Ind Ltd | Pilot nozzle, gas turbine combustion chamber equipped therewith, and gas turbine |
| JP2016505131A (en) * | 2013-02-05 | 2016-02-18 | シーメンス アクティエンゲゼルシャフト | Fuel lance with thermal insulation layer |
-
1994
- 1994-02-23 JP JP06025121A patent/JP3082823B2/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009047414A (en) * | 2007-08-21 | 2009-03-05 | General Electric Co <Ge> | Fuel nozzle and diffusion tip for the fuel nozzle |
| JP2012149878A (en) * | 2011-01-18 | 2012-08-09 | General Electric Co <Ge> | Gas turbine combustor end cover assembly equipped with integrated flow throttle and manifold sealing |
| JP2013178035A (en) * | 2012-02-28 | 2013-09-09 | Mitsubishi Heavy Ind Ltd | Pilot nozzle, gas turbine combustion chamber equipped therewith, and gas turbine |
| JP2016505131A (en) * | 2013-02-05 | 2016-02-18 | シーメンス アクティエンゲゼルシャフト | Fuel lance with thermal insulation layer |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3082823B2 (en) | 2000-08-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4655044A (en) | Coated high temperature combustor liner | |
| EP1564495B1 (en) | Combustor assembly and method for making a combustor assembly | |
| US6286302B1 (en) | Venturi for use in the swirl cup package of a gas turbine combustor having water injected therein | |
| CN101331246A (en) | Method for coating a blade and blade of a gas turbine | |
| US5009070A (en) | Combustion apparatus for gas turbine | |
| JPH0715141B2 (en) | Heat resistant parts | |
| JP2826824B2 (en) | Thermal insulation coating method and gas turbine combustor | |
| JPH07233946A (en) | Heat resistance and anticorrosion treated combustor nozzle for gas turbine | |
| RU2433346C2 (en) | Method to increase durability and improve characteristics of flare tip, flare tip | |
| US5780106A (en) | Method for low temperature aluminum coating of an article | |
| US8708658B2 (en) | Local application of a protective coating on a shrouded gas turbine engine component | |
| JPS62210329A (en) | Ceramic coated heat-resistant material and manufacture thereof | |
| JPH11131206A (en) | Powder material for thermal spraying coating and high temperature member using the same | |
| US20180355477A1 (en) | Thermal coating system with aluminide | |
| JPS6220672A (en) | Fuel valve atomizer for internal-combustion engine | |
| KR930002869B1 (en) | Heat-resisting tube for annealing furnace and process for making | |
| JP2977389B2 (en) | Gas turbine hot parts coatings | |
| JP2001004101A (en) | Unit member for water-cooled panel segment and manufacture of water-cooled panel segment with protective coating | |
| CN106567034B (en) | The super thick metal-cermic coating of resistance to heat plasma and preparation method | |
| JP2002309999A (en) | Cylinder head repair method for internal combustion engine | |
| JPH0610354B2 (en) | Ceramic coated heat resistant member and method for manufacturing the same | |
| JPH1054516A (en) | Gasifying furnace burner | |
| CN111566410A (en) | Burner with slurry coating having high resistance to metal dust | |
| JPH09257190A (en) | Surface treatment of boiler tube | |
| JPH02290925A (en) | Method for nonoxidatively heating band steel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20000523 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090630 Year of fee payment: 9 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20100630 Year of fee payment: 10 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20100630 Year of fee payment: 10 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110630 Year of fee payment: 11 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110630 Year of fee payment: 11 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120630 Year of fee payment: 12 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20130630 Year of fee payment: 13 |
|
| EXPY | Cancellation because of completion of term |