JP3082823B2 - Gas turbine combustor nozzle with heat and corrosion resistance treatment - Google Patents
Gas turbine combustor nozzle with heat and corrosion resistance treatmentInfo
- Publication number
- JP3082823B2 JP3082823B2 JP06025121A JP2512194A JP3082823B2 JP 3082823 B2 JP3082823 B2 JP 3082823B2 JP 06025121 A JP06025121 A JP 06025121A JP 2512194 A JP2512194 A JP 2512194A JP 3082823 B2 JP3082823 B2 JP 3082823B2
- Authority
- JP
- Japan
- Prior art keywords
- nozzle
- heat
- gas turbine
- corrosion resistance
- turbine combustor
- 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.)
- Expired - Lifetime
Links
Landscapes
- Coating By Spraying Or Casting (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
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 is applicable to a burner component such as a boiler.
【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 nozzle structure in a conventional gas turbine combustor is shown in FIG. 5, and a fuel nozzle hole 2 through which oil fuel or gas fuel passes is provided in a nozzle body 1, and the fuel nozzle hole 2 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 from the fuel nozzle hole 2,
The air is blown out from the nozzle tip through an air nozzle hole 3 passing 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易
く、このため未燃成分（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
記材質の変更により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、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局部的に表面
処理することにより、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 tends to stagnate in the central portion of the fuel nozzle hole 2 and the air nozzle hole 3 which are surrounded by the front-end ejection portions. (E.g., carbon content) and tends to become hot due to the heat of the high-temperature flame. As a result,
In many cases, damage due to high-temperature oxidation or high-temperature corrosion occurs at the central portion of the nozzle tip, thereby significantly reducing the durability of the entire nozzle. For this reason, it has been attempted to change the nozzle to a material having excellent heat resistance, or to perform a heat-resistant surface treatment on the entire nozzle, but any of these causes an increase in cost, and it is also attempted to improve the heat resistance by changing the material. Then, the material itself tends to be hardened, and various problems such as deterioration in workability of the nozzle have occurred. Therefore, the present invention provides a nozzle tip
Only the part corresponding to the stagnation part of the combustion gas is locally surfaced
By processing, it solves the problems of conventional nozzles, and aims to provide a low-cost, long-life gas turbine combustor nozzle that is excellent in heat resistance and corrosion resistance and can reduce damage at the center of the nozzle. .
【０００４】[0004]
【課題を解決するための手段】このため本発明は、メッ
キ、Ｎｉ−Ｃｒ合金溶射或いはＡｌ−Ｓｉスラリーコー
ティングの比較的熱影響の少ない表面処理法により、ノ
ズル先端の燃焼ガスのよどみ部に相当する部分のみを局
部的に表面処理し、ノズル自体の耐熱、耐久性を増加す
るようにしてなるもので、これを課題解決のための手段
とするものである。SUMMARY OF THE INVENTION Accordingly, the present invention provides a novel method of surface treatment by plating, Ni-Cr alloy spraying or Al-Si slurry coating, which has a relatively low thermal effect.
Only the part corresponding to the stagnation part of the combustion gas at the tip of
Partially surface-treated to increase the heat resistance and durability of the nozzle itself
Those obtained by the so that, it is an unit for which a problem solution.
【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。According to the present invention, the nozzle body is made of a conventional material (SUS30).
4)) and after the fabrication method, in order to plate only the portion corresponding to the stagnation portion of the combustion gas at the tip of the nozzle, masking is applied to the portion other than the plating portion, and the tip of the nozzle is immersed in a predetermined plating solution. By forming amorphous chromium plating of about 5 μm, the nozzle body is made of the same material as the conventional method. Therefore, it is only necessary to add a step of processing only the nozzle tip without basically changing the nozzle manufacturing method or the like. Therefore, a reduction in processing cost can be realized, and a long-life gas turbine combustion nozzle excellent in heat resistance and corrosion resistance can be provided. In the present invention, as a surface treatment method of the nozzle tip, other than plating, plasma spraying of Ni-Cr alloy or Al-
There are those using 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, a masking 10 is applied to a portion other than a portion where a plating process is performed on a nozzle body 1 made of a metal or the like, and then immersed in a plating solution 20 to obtain a film thickness of about 5 μm under the conditions shown in Table 1. Chrome plating was performed.
【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 subjected to masking 10 with a heat-resistant tape on a portion other than a portion to be surface-treated, and then, the sprayed surface is roughened by grid blasting to promote fixing of the sprayed material. Then, plasma spraying 30 was performed on a 50Ni-5Cr alloy with a target thickness of about 100 μm, and a layer of a 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)> As in the first specific example, a masking 10 is applied to a portion other than the coating portion as shown in FIG. And so on, 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 maintained at about 120 ° C. for 2 hours to perform primary drying. Next, after removing the masking tape and performing secondary drying at 350 to 400 ° C. for 2 hours, heat treatment 60 was performed at 850 ° C. for 3 hours in a 3% H 2 —N 2 gas atmosphere. After heat treatment, the nozzle coated with slurry was blasted with glass beads.
0, and the residue of the slurry was removed to form an Al-Si diffusion layer 80, thereby obtaining a product. In addition, you may process by ceramic slurry coating 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。[0009] The SUS304 of the nozzle body is moved to the nozzle tip by each surface treatment of the nozzle tip according to the above specific example.
The surface treatment of such a material having excellent heat resistance and corrosion resistance significantly reduced the corrosion rate due to high-temperature oxidation and high-temperature corrosion of the tip, and extended the life of the entire nozzle. The conventional one was replaced in about one year, but could be extended to about two years for chromium-plated ones and about three years for thermal spraying and treatment with Al-Si slurry. In addition, since only the required portion at the nozzle tip is processed, deformation and blockage of the fuel nozzle hole and air nozzle hole due to the surface treatment can be prevented, and the processing cost is reduced to about 1/2 to 1 compared to the entire processing.
/ 3. In addition, since the basic nozzle material and structure are the same as the conventional one, there is no need to change the nozzle manufacturing method, etc. Further, any of the surface treatment methods can reduce the thermal effect on the material to be treated relatively, so that the distortion due to the surface treatment And the like can be suppressed.
【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 a high-temperature oxidation test of a surface-treated portion according to each embodiment of the present invention. In a test at 900 ° C. for 1,000 hours in the atmosphere, which is the maximum temperature at which the nozzle can be used, the oxidation amount of the product of the present invention was about 1/10 to 1/5 of that of the conventional material SUS304 or the like, showing excellent oxidation resistance. . Further, based on the above results, it was applied to the nozzle portion of an actual gas turbine that is performing gas combustion such as LPG, and a trial for one year (approximately 7,500 hours), which is a periodic inspection period of the plant, was performed. Unprocessed products)
At the nozzle tip, the overlay must be repaired or replaced.
While the thickness was reduced by 1 to 0.2 mm, all of Examples 1 to 3 of the present invention did not show any signs of the thickness reduction and maintained a healthy state.
【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、Ｎ
ｉ−Ｃｒ合金溶射或いはＡｌ−Ｓｉスラリーコーティン
グ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
先端の燃焼ガスのよどみ部に相当する部分のみを局部的
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, plating, N
By the surface treatment method of i-Cr alloy spraying or Al-Si slurry coating with relatively little heat effect, only the heat receiving part at the tip of the nozzle is locally surface-treated to increase the heat resistance and durability of the nozzle itself, Excellent heat resistance,
It is possible to dramatically reduce damage at the center of the nozzle, and to locally treat only the portion corresponding to the stagnation portion of the combustion gas at the tip of the nozzle. It can be provided.
【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 view showing a nozzle manufactured 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 view showing a nozzle manufactured 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 diagram illustrating a nozzle manufactured 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 a high-temperature oxidation test result 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 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 DESCRIPTION OF SYMBOLS 1 Nozzle main body 10 Masking 20 Plating solution 30 Plasma spraying 40 Ni-Cr alloy 50 Al-Si slurry 60 Heat treatment 70 Glass bead blast 80 Al-Si diffusion layer
───────────────────────────────────────────────────── フロントページの続き (58)調査した分野(Int.Cl.7，ＤＢ名) F23R 3/00 F02C 7/00 ──────────────────────────────────────────────────続 き Continued on front page (58) Field surveyed (Int. Cl. 7 , DB name) F23R 3/00 F02C 7/00
Claims (1)
−Ｓｉスラリーコーティングの比較的熱影響の少ない表
面処理法により、ノズル先端の燃焼ガスのよどみ部に相
当する部分のみを局部的に表面処理し、ノズル自体の耐
熱、耐久性を増加するようにしたことを特徴とする耐
熱、耐食処理を施したガスタービン用燃焼器ノズル。1. Plating, Ni-Cr alloy spraying or Al
-The surface treatment method of Si slurry coating, which has relatively little thermal effect, makes it possible to
A combustor nozzle for a gas turbine which has been subjected to heat and corrosion resistance treatment, in which only the corresponding portion is locally surface-treated to increase the heat resistance and durability of the nozzle itself.
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 JPH07233946A (en) | 1995-09-05 |
| JP3082823B2 true 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) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7861528B2 (en) * | 2007-08-21 | 2011-01-04 | General Electric Company | Fuel nozzle and diffusion tip therefor |
| US8820086B2 (en) * | 2011-01-18 | 2014-09-02 | General Electric Company | Gas turbine combustor endcover assembly with integrated flow restrictor and manifold seal |
| JP5967974B2 (en) * | 2012-02-28 | 2016-08-10 | 三菱日立パワーシステムズ株式会社 | Pilot nozzle, gas turbine combustor including the same, and gas turbine |
| WO2014121998A1 (en) * | 2013-02-05 | 2014-08-14 | Siemens Aktiengesellschaft | Fuel lances having thermally insulating coating |
-
1994
- 1994-02-23 JP JP06025121A patent/JP3082823B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH07233946A (en) | 1995-09-05 |
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