JPS62178702A - Turbine blade - Google Patents
Turbine bladeInfo
- Publication number
- JPS62178702A JPS62178702A JP1854886A JP1854886A JPS62178702A JP S62178702 A JPS62178702 A JP S62178702A JP 1854886 A JP1854886 A JP 1854886A JP 1854886 A JP1854886 A JP 1854886A JP S62178702 A JPS62178702 A JP S62178702A
- Authority
- JP
- Japan
- Prior art keywords
- short fiber
- turbine blade
- root portion
- blade
- blade root
- 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
- 239000000463 material Substances 0.000 claims abstract description 14
- 239000000835 fiber Substances 0.000 claims abstract description 10
- 239000011159 matrix material Substances 0.000 claims abstract description 6
- 239000000203 mixture Substances 0.000 claims abstract description 5
- 239000000843 powder Substances 0.000 claims abstract description 5
- 239000003733 fiber-reinforced composite Substances 0.000 claims abstract description 4
- 229910052751 metal Inorganic materials 0.000 claims description 5
- 239000002184 metal Substances 0.000 claims description 5
- 239000012779 reinforcing material Substances 0.000 claims description 2
- 239000011247 coating layer Substances 0.000 abstract description 5
- 238000005299 abrasion Methods 0.000 abstract description 3
- 239000011248 coating agent Substances 0.000 abstract description 2
- 238000000576 coating method Methods 0.000 abstract description 2
- 230000002787 reinforcement Effects 0.000 abstract description 2
- 239000002131 composite material Substances 0.000 description 7
- 229910045601 alloy Inorganic materials 0.000 description 4
- 239000000956 alloy Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000010791 quenching Methods 0.000 description 2
- 230000000171 quenching effect Effects 0.000 description 2
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 235000014036 Castanea Nutrition 0.000 description 1
- 241001070941 Castanea Species 0.000 description 1
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- 229910052581 Si3N4 Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000001010 compromised effect Effects 0.000 description 1
- NJLLQSBAHIKGKF-UHFFFAOYSA-N dipotassium dioxido(oxo)titanium Chemical compound [K+].[K+].[O-][Ti]([O-])=O NJLLQSBAHIKGKF-UHFFFAOYSA-N 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は内燃機関のピストンやシリンダおよびジェット
エンジンや蒸気、ガスタービンの動翼などに被覆層とし
て適用される複合材料に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a composite material that is applied as a coating layer to pistons and cylinders of internal combustion engines, and rotor blades of jet engines, steam, and gas turbines.
従来タービン翼の付け根は、翼の回転にょうて発生する
遠心力と微少な応力変動によって７レツテイング摩耗が
発生し、これを防止するために焼入れ等による表面硬化
処理が採られてきた。Conventionally, at the root of a turbine blade, retting wear occurs due to centrifugal force and minute stress fluctuations generated as the blade rotates, and to prevent this, surface hardening treatment such as quenching has been adopted.
ところが、焼入れによる表面硬化を行うと。 However, when the surface is hardened by quenching.
靭性が損なわれ、また母材の材料によっては。Toughness is compromised and also depends on the base material.
充分に焼入れによる効果が得られないもの、あるいは熱
処理による硬化が難しいものもあって非常に不具合であ
った。There were some cases in which the effect of hardening could not be obtained sufficiently, or in some cases it was difficult to harden by heat treatment, which was very inconvenient.
タービン翼々根部の耐摩耗性を向上させしかも、靭性そ
の他の必要特性を損なわない方法として本発明では、タ
ービン翼々根部分表面と。In the present invention, as a method for improving the wear resistance of the roots of turbine blades without impairing toughness and other necessary properties, the present invention provides a method for improving the wear resistance of the roots of turbine blades without impairing toughness and other necessary properties.
同翼根部分が嵌挿されるディスクの翼取り付け部分台０
俵面との双方もしくはいずれか一方に。The blade attachment part base 0 of the disk into which the blade root part is inserted
Either or both sides of the bale surface.
マド１７ツクスとなる金属粉末と、短繊維強化材料とを
混合してレーザービームを用いて溶融凝固；−で短繊維
強化複合材料を被覆したことてある。A short fiber-reinforced composite material has been coated with a mixture of metal powder to be made of mud and a short fiber-reinforced material and melted and solidified using a laser beam.
短繊維強化複合材料は靭性が犬きく、耐摩耗性に優れて
いる。「さらに、複合材料を製造するためにマトリック
スとなる金属粉末と短繊維強化材との混合物をレーザー
ビームを用いて溶融凝固したので、均質な複合材料の被
覆層を複雑な形状の表面に形成することが可能である。Short fiber reinforced composite materials have excellent toughness and wear resistance. "Furthermore, in order to manufacture the composite material, we melted and solidified the mixture of matrix metal powder and short fiber reinforcement using a laser beam, which enabled us to form a homogeneous composite coating layer on the complex-shaped surface. Is possible.
」〔実施例〕
第１図は本発明に係る一実施例として、蒸気タービン動
翼々根部分に複合材料の被覆層を形成させた例を示す概
略説明図である。複合材料の強化材となる短繊維１は、
予めマトリックスとなる粉末状の合金２と混合させ、こ
れらの混給し溶融凝固させた。複合材料の被覆層は凝固
後、研磨等によって仕上げ加工後２図示省略のディスク
に取り付けた。[Embodiment] FIG. 1 is a schematic explanatory diagram showing an example in which a coating layer of a composite material is formed on the roots of steam turbine rotor blades as an embodiment of the present invention. The short fiber 1 that serves as a reinforcing material for the composite material is
It was mixed in advance with powdered Alloy 2, which would serve as a matrix, and the mixture was mixed and melted and solidified. After the coating layer of the composite material was solidified, it was finished by polishing or the like and then attached to two disks (not shown).
なお、レーザー照射条件は出力３ ＫＷ照射速度３ｍ／
頗としだ。The laser irradiation conditions are output 3, KW irradiation speed 3m/
Chestnut and toshida.
また、短繊維には炭化けい素、窒化けい素。In addition, short fibers include silicon carbide and silicon nitride.
酸化アルミニウム、チタン酸カリウムなどのセラミック
ス繊維やタングステン、モリブデンなどの金属繊維もし
くはこれらのウィスカーを用い、マトリックスとなる金
属には、タービン翼材として用いられる低合金鋼、Ｔｉ
合金のほか耐摩性の良好なＣＯ基耐摩耗合金の粉末を
用いる。朦維含有量は素材の材質に応じて最適量が決定
されるが、少なくとも５％以上必要であり４０％を越え
ると脆化などが生じるためこの間とする。Ceramic fibers such as aluminum oxide and potassium titanate, metal fibers such as tungsten and molybdenum, or their whiskers are used, and the matrix metal is low alloy steel, Ti, which is used as a turbine blade material.
In addition to the alloy, powder of a CO-based wear-resistant alloy with good wear resistance is used. The optimal amount of fiber content is determined depending on the material of the material, but it is necessary to be at least 5%, and if it exceeds 40%, embrittlement will occur, so it should be within this range.
本発明になる素材のすベシ摩耗試験結果を第１表に示す
が未処理材に対し２本発明材の摩耗とが確認できた。Table 1 shows the results of the overall abrasion test for the material of the present invention, and it was confirmed that two of the materials of the present invention were worn out compared to the untreated material.
第１表 すべり摩耗試験結果
試験条件 摩擦速度 ０．２４ｍ／ｓｅｃ摩擦距離 ５
０００ｍ
相手材 ｔ３Ｃｒ−Ｍｏ鋼
無潤滑 水冷
〔発明の効果〕
タービン動翼々根部の嵌挿部に複合材料被覆一層を形成
することにより、耐フレツテイング摩耗性が著しく改善
される等本発明は産業の発達に寄与するところが大きい
。Table 1 Sliding wear test results Test conditions Friction speed 0.24m/sec Friction distance 5
000m Compatible material: t3Cr-Mo steel, non-lubricated, water-cooled [Effects of the invention] By forming a single layer of composite material coating on the fitting portion of the roots of the turbine rotor blades, the fretting wear resistance is significantly improved, etc. The present invention is a development of industry. It has a large contribution to make.
第１図は本発明に係る一実施例としての概略を示すター
ビン動翼の製作手順を示す説明図である。
１・・・短繊維、２・・・マトリックスとなる粉末状の
合金、３・・・フィーダ、４・・・タービン動翼。
５・・・レーザービーム。FIG. 1 is an explanatory diagram showing an outline of a manufacturing procedure of a turbine rotor blade as an embodiment of the present invention. DESCRIPTION OF SYMBOLS 1... Short fiber, 2... Powdered alloy serving as a matrix, 3... Feeder, 4... Turbine rotor blade. 5... Laser beam.
Claims (1)
ディスクの翼取り付け部分表面との双方もしくはいずれ
か一方にマトリックスとなる金属粉末と、短繊維強化材
料とを混合して、レーザービームを用いて溶融凝固した
短繊維強化複合材が被覆されてなることを特徴とするタ
ービン翼。A metal powder serving as a matrix and a short fiber reinforcing material are mixed on the surface of the turbine blade root portion and/or the surface of the blade attachment portion of the disk into which the blade root portion is inserted, and a laser beam is used to mix the mixture with a short fiber reinforced material. A turbine blade characterized by being coated with a short fiber-reinforced composite material melted and solidified.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1854886A JPS62178702A (en) | 1986-01-30 | 1986-01-30 | Turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1854886A JPS62178702A (en) | 1986-01-30 | 1986-01-30 | Turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62178702A true JPS62178702A (en) | 1987-08-05 |
Family
ID=11974682
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1854886A Pending JPS62178702A (en) | 1986-01-30 | 1986-01-30 | Turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62178702A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0578999U (en) * | 1992-04-02 | 1993-10-26 | 石川島播磨重工業株式会社 | Moving wings |
| JP2011033037A (en) * | 2009-08-04 | 2011-02-17 | Siemens Ag | Thermoplastic final stage blade |
-
1986
- 1986-01-30 JP JP1854886A patent/JPS62178702A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0578999U (en) * | 1992-04-02 | 1993-10-26 | 石川島播磨重工業株式会社 | Moving wings |
| JP2011033037A (en) * | 2009-08-04 | 2011-02-17 | Siemens Ag | Thermoplastic final stage blade |
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