JPH1122407A - Gas turbine blade - Google Patents
Gas turbine bladeInfo
- Publication number
- JPH1122407A JPH1122407A JP17409897A JP17409897A JPH1122407A JP H1122407 A JPH1122407 A JP H1122407A JP 17409897 A JP17409897 A JP 17409897A JP 17409897 A JP17409897 A JP 17409897A JP H1122407 A JPH1122407 A JP H1122407A
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- turbine blade
- metal plate
- ceramic layer
- plate piece
- 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.)
- Pending
Links
- 239000000919 ceramic Substances 0.000 claims abstract description 23
- 239000002184 metal Substances 0.000 claims abstract description 20
- 239000000463 material Substances 0.000 claims abstract description 17
- 239000000203 mixture Substances 0.000 claims abstract description 5
- 239000000956 alloy Substances 0.000 claims abstract description 4
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 4
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 239000006185 dispersion Substances 0.000 abstract 2
- 229910010293 ceramic material Inorganic materials 0.000 description 5
- 230000007797 corrosion Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 3
- 230000008646 thermal stress Effects 0.000 description 3
- 229910052581 Si3N4 Inorganic materials 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 description 2
- 238000005524 ceramic coating Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、耐熱性、耐酸化性
及び耐食性等が要求されるガスタービン翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine blade requiring heat resistance, oxidation resistance, corrosion resistance, and the like.
【０００２】[0002]
【従来の技術】従来のガスタービン翼においては、耐熱
性、耐酸化性及び耐食性を増してその寿命を延ばすため
に、表面にセラミックスのコーティングが施されるよう
になってきた。2. Description of the Related Art In conventional gas turbine blades, a ceramic coating has been applied to the surface thereof in order to increase the heat resistance, oxidation resistance and corrosion resistance and extend the life thereof.
【０００３】このガスタービン翼のコーティング用のセ
ラミックスは、各種組成のものが使用されているが、一
般には、高温強度に優れ、しかも靭性も比較的高く、耐
熱衝撃性にも優れているシリコンナイトライト（窒化珪
素：Ｓｉ3 Ｎ4 ）が使われている。[0003] As the ceramics for coating the gas turbine blades, various compositions are used. In general, silicon nitride having excellent high-temperature strength, relatively high toughness and excellent thermal shock resistance is used. Light (silicon nitride: Si 3 N 4 ) is used.
【０００４】[0004]
【発明が解決しようとする課題】セラミックス材は、入
口温度が高温化する傾向にあるガスタービンの翼材とし
て、非常に有望な材料である。A ceramic material is a very promising material as a blade material for a gas turbine whose inlet temperature tends to increase.
【０００５】このセラミックス材は、金属材料と比較す
ると、次の長所がある。即ち、（１）高温強度が高く、
（２）耐摩耗性が優れている、（３）耐食性が優れてい
る、（４）軽量である、（５）熱膨張係数が小さいなど
である。しかしながら、セラミックス材には次のような
短所もある。The ceramic material has the following advantages as compared with the metal material. That is, (1) high temperature strength is high,
(2) excellent wear resistance; (3) excellent corrosion resistance; (4) light weight; and (5) small thermal expansion coefficient. However, ceramic materials also have the following disadvantages.
【０００６】（１）脆いために微細な欠陥があっても破
壊につながる、（２）硬いために機械加工が難しい、
（３）熱膨張係数が小さいために金属との接合が難し
い、（４）寸法や製造条件により強度が大きく影響され
る、（５）高価であるなどである。[0006] (1) Even if there is a minute defect due to brittleness, it leads to destruction; (2) Hardness makes machining difficult;
(3) It is difficult to bond with metal due to a small coefficient of thermal expansion, (4) Strength is greatly affected by dimensions and manufacturing conditions, and (5) it is expensive.
【０００７】従来のガスタービンにおいて、セラミック
ス材を用いた翼とした場合、上記のようなセラミックス
材の特性から品質にバラツキが生じて、強度の高い一定
の製品を作るのが困難であった。本発明は，上記の課題
を解決しようとするものである。In a conventional gas turbine, when a blade made of a ceramic material is used, the quality varies due to the characteristics of the ceramic material as described above, and it has been difficult to produce a high-strength product. The present invention seeks to solve the above problems.
【０００８】[0008]
【課題を解決するための手段】本発明のガスタービン翼
は、組成及び特性が翼母材に近似しかつ熱膨張係数が翼
母材よりも低い耐熱合金よりなる金属プレート片と、同
金属プレート片の表面にコーティングされて形成された
セラミックス層とをそれぞれ備えた複数個の分割セグメ
ントが、その接ガス面を覆うように配設されその面に固
定されたことを特徴としている。SUMMARY OF THE INVENTION A gas turbine blade according to the present invention comprises a metal plate piece made of a heat-resistant alloy having a composition and characteristics similar to those of a blade base material and having a coefficient of thermal expansion lower than that of the blade base material; A plurality of divided segments each having a ceramic layer formed by coating the surface of a piece are arranged so as to cover the gas contact surface and fixed to the surface.
【０００９】上記において、金属プレート片の表面は小
面積のため、安定したセラミックス層を形成することが
でき、品質のバラツキは解消され、高品質のガスタービ
ン翼を形成することが可能となる。In the above, since the surface of the metal plate piece has a small area, a stable ceramic layer can be formed, the variation in quality is eliminated, and a high-quality gas turbine blade can be formed.
【００１０】また、分割セグメントが小片のため、金属
プレート片とセラミックス層との熱膨張差は容易に吸収
され、セラミックス層での熱応力によるクラックの発生
が防止可能となる。Further, since the divided segments are small pieces, the difference in thermal expansion between the metal plate piece and the ceramic layer can be easily absorbed, and cracks due to thermal stress in the ceramic layer can be prevented.
【００１１】[0011]
【発明の実施の形態】本発明の実施の一形態に係るガス
タービン翼について、図１により説明する。図１に示す
本実施形態に係るガスタービン翼は、図１（ａ）に示す
ようにガスタービン翼の翼部７とその上下のシュラウド
８，９の接ガス面全体を覆うように配設された複数個の
分割セグメント２を備えている。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A gas turbine blade according to an embodiment of the present invention will be described with reference to FIG. The gas turbine blade according to the present embodiment shown in FIG. 1 is disposed so as to cover the entire gas contact surfaces of the blade portion 7 of the gas turbine blade and the upper and lower shrouds 8 and 9 as shown in FIG. A plurality of divided segments 2.
【００１２】上記分割セグメント２は、図１（ｂ）に示
すように、組成及び特性がガスタービン翼の母材１と近
似しかつ熱膨張係数が母材１よりも低い耐熱合金よりな
る金属プレート片３と、この金属プレート片３の表面に
コーティングされたセラミックス層４と、図１（ｃ）に
示すように上記金属プレート片３の裏面に溶接接合１０
されたボルト５を備え、このボルト５を母材１に設けら
れた穴１ａに貫通させ、ボルト５にナット６を螺合させ
ることにより母材１に固定される。As shown in FIG. 1B, the divided segment 2 is made of a metal plate made of a heat-resistant alloy whose composition and characteristics are close to those of the base material 1 of the gas turbine blade and whose thermal expansion coefficient is lower than that of the base material 1. 1, a ceramic layer 4 coated on the surface of the metal plate piece 3, and a welding joint 10 on the back surface of the metal plate piece 3 as shown in FIG.
The bolt 5 is fixed to the base material 1 by passing the bolt 5 through a hole 1 a provided in the base material 1 and screwing a nut 6 to the bolt 5.
【００１３】上記において、分割セグメント２を形成す
る金属プレート片３の表面は小面積のため、それぞれの
表面には安定したセラミックス層４を形成することが可
能となり、セラミックス層４の品質のバラツキが解消さ
れ、高品質のガスタービン翼を得ることが可能となっ
た。In the above, since the surface of the metal plate piece 3 forming the divided segment 2 has a small area, a stable ceramic layer 4 can be formed on each surface, and the quality of the ceramic layer 4 varies. The problem has been solved, and a high-quality gas turbine blade can be obtained.
【００１４】また、それぞれの分割セグメント２は小片
のため、金属プレート片３とセラミックス層４との間に
熱膨張量の差が発生してもその差の絶対値が小さく、熱
応力によるセラミックス層４への衝撃的な作用は吸収さ
れ、セラミックス層４におけるクラックの発生を防止す
ることが可能となった。Since each of the divided segments 2 is a small piece, even if a difference in the amount of thermal expansion occurs between the metal plate piece 3 and the ceramic layer 4, the absolute value of the difference is small, and the ceramic layer due to thermal stress is small. The impact on the ceramic layer 4 was absorbed, and cracks in the ceramic layer 4 could be prevented.
【００１５】本発明の実施の他の形態に係るガスタービ
ン翼について、図２により説明する。図２に示す本実施
形態に係るガスタービン翼は、上記一実施形態における
金属プレート片３に溝１１が設けられ、また、ボルト５
に頭部１２が設けられ、ボルト５に設けられたおねじが
母材１の穴１ａの内面に設けられためねじと螺合するも
のである。A gas turbine blade according to another embodiment of the present invention will be described with reference to FIG. The gas turbine blade according to the present embodiment shown in FIG. 2 has a groove 11 provided in the metal plate piece 3 in the above-described embodiment and a bolt 5
A head 12 is provided on the base member 1, and a male screw provided on the bolt 5 is provided on the inner surface of the hole 1a of the base material 1 so as to screw with the screw.
【００１６】本実施形態においては、頭部１２を金属プ
レート片３の溝１１に挿入した後、ボルト５を回転させ
ることにより、上記一実施形態と同様、分割セグメント
２を母材１に固定することができる。In this embodiment, after the head 12 is inserted into the groove 11 of the metal plate piece 3 and the bolt 5 is rotated, the divided segment 2 is fixed to the base material 1 as in the above-described embodiment. be able to.
【００１７】[0017]
【発明の効果】本発明のガスタービン翼は、金属プレー
ト片と、その面にコーティングされたセラミックス層と
を備えた分割セグメントが複数個形成され、それぞれの
分割セグメントがガスタービン翼の接ガス面を覆うよう
に配設されその面に固定されたものとしたことによっ
て、上記分割セグメントの表面が小面積のため、品質の
バラツキの少い高品質のセラミックス層の形成が可能に
なるとともに、金属プレート片とセラミックス層との熱
膨張量の差により発生する熱応力によるセラミックス層
の破損の防止が可能となり、ガスタービン翼の信頼性が
一段と向上するとともに、ガスタービンの高温化への対
応が可能となる。According to the gas turbine blade of the present invention, a plurality of divided segments each having a metal plate piece and a ceramic layer coated on the surface thereof are formed, and each divided segment is formed on a gas contact surface of the gas turbine blade. Is arranged so as to cover the surface, and the surface of the divided segment is small, so that it is possible to form a high-quality ceramic layer with little variation in quality, and It is possible to prevent the ceramic layer from being damaged due to the thermal stress generated by the difference in the amount of thermal expansion between the plate piece and the ceramic layer, further improving the reliability of the gas turbine blade and responding to the high temperature of the gas turbine. Becomes
【図１】本発明の実施の一形態に係るガスタービン翼の
説明図で、（ａ）は全体斜視図、（ｂ）は母材に分割セ
グメントを取付けた状態の断面図、（ｃ）はボルトの金
属プレート片への取付け状態を示す斜視図である。1A and 1B are explanatory views of a gas turbine blade according to an embodiment of the present invention, in which FIG. 1A is an overall perspective view, FIG. 1B is a cross-sectional view of a state where a divided segment is attached to a base material, and FIG. It is a perspective view which shows the attachment state of the bolt to the metal plate piece.
【図２】本発明の実施の他の形態に係るガスタービン翼
の説明図で、（ａ）は母材に分割セグメントを取付けた
状態の断面図、（ｂ）はボルトの金属プレート片への取
付け状態を示す斜視図である。FIGS. 2A and 2B are explanatory views of a gas turbine blade according to another embodiment of the present invention, in which FIG. 2A is a cross-sectional view showing a state in which a divided segment is attached to a base material, and FIG. It is a perspective view which shows an attachment state.
１ 母材 １ａ 穴 ２ 分割セグメント ３ 金属プレート片 ４ セラミックス層 ５ ボルト ６ ナット ７ 翼部 ８，９ シュラウド １０ 溶接接合 １１ 溝 １２ 頭部 Reference Signs List 1 base material 1a hole 2 divided segment 3 metal plate piece 4 ceramic layer 5 bolt 6 nut 7 wing 8,9 shroud 10 welded joint 11 groove 12 head
Claims (1)
張係数が翼母材よりも低い耐熱合金よりなる金属プレー
ト片と、同金属プレート片の表面にコーティングされて
形成されたセラミックス層とをそれぞれ備えた複数個の
分割セグメントが、その接ガス面を覆うように配設され
その面に固定されたことを特徴とするガスタービン翼。1. A metal plate piece made of a heat-resistant alloy having a composition and properties similar to those of a wing base material and having a lower coefficient of thermal expansion than that of the wing base material, and a ceramic layer formed by coating the surface of the metal plate piece. And a plurality of divided segments each comprising: a gas turbine blade that is disposed so as to cover a gas contact surface thereof and is fixed to the surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17409897A JPH1122407A (en) | 1997-06-30 | 1997-06-30 | Gas turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17409897A JPH1122407A (en) | 1997-06-30 | 1997-06-30 | Gas turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH1122407A true JPH1122407A (en) | 1999-01-26 |
Family
ID=15972622
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP17409897A Pending JPH1122407A (en) | 1997-06-30 | 1997-06-30 | Gas turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH1122407A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPWO2003048528A1 (en) * | 2001-11-30 | 2005-04-14 | 株式会社日立製作所 | Method for repairing blades of gas turbine for power generation and turbine blades after repair |
-
1997
- 1997-06-30 JP JP17409897A patent/JPH1122407A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPWO2003048528A1 (en) * | 2001-11-30 | 2005-04-14 | 株式会社日立製作所 | Method for repairing blades of gas turbine for power generation and turbine blades after repair |
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Legal Events
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|---|---|---|---|
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| A521 | Written amendment |
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