JPS6240525B2 - - Google Patents
Info
- Publication number
- JPS6240525B2 JPS6240525B2 JP9065583A JP9065583A JPS6240525B2 JP S6240525 B2 JPS6240525 B2 JP S6240525B2 JP 9065583 A JP9065583 A JP 9065583A JP 9065583 A JP9065583 A JP 9065583A JP S6240525 B2 JPS6240525 B2 JP S6240525B2
- Authority
- JP
- Japan
- Prior art keywords
- leading edge
- rotor blade
- edge member
- wear
- blade base
- 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
Links
- 239000002245 particle Substances 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 239000000919 ceramic Substances 0.000 claims description 3
- 239000011159 matrix material Substances 0.000 claims description 3
- 239000010881 fly ash Substances 0.000 description 4
- 230000003628 erosive effect Effects 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 229910001208 Crucible steel Inorganic materials 0.000 description 1
- 229910001347 Stellite Inorganic materials 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- AHICWQREWHDHHF-UHFFFAOYSA-N chromium;cobalt;iron;manganese;methane;molybdenum;nickel;silicon;tungsten Chemical compound C.[Si].[Cr].[Mn].[Fe].[Co].[Ni].[Mo].[W] AHICWQREWHDHHF-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000005552 hardfacing Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000004383 yellowing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
【発明の詳細な説明】
〔発明の利用分野〕
本発明は摩耗性のある微粒子を含むガスを扱う
軸流フアンの耐摩耗動翼に係り、特に石炭火力プ
ラント用の排風機のような耐アツシユエロージヨ
ン性の必要な軸流フアンに使用して好適な耐摩耗
動翼に関する。[Detailed Description of the Invention] [Field of Application of the Invention] The present invention relates to a wear-resistant rotor blade for an axial flow fan that handles gas containing abrasive particles, and in particular to a wear-resistant rotor blade for an axial flow fan that handles gas containing abrasive particles, and particularly for use in abrasion-resistant rotor blades such as exhaust fans for coal-fired power plants. The present invention relates to a wear-resistant rotor blade suitable for use in an axial flow fan that requires yellowing properties.
石炭火力プラントにおける排風機は、フライア
ツシユを含んだボイラからの燃焼排ガスを取扱う
ため、このフライアツシユにより流路部分が摩耗
するが、特に高速で回転する動翼の摩耗が激しく
なる。この動翼の摩耗状況を軸流フアンの動翼を
例にとつて第１図及び第２図により説明する。第
１図は動翼の側面図、第２図は第１図の−矢
視断面図を示し、矢印方向に流れるガス中のフラ
イアツシユは高速で動翼母体１の前縁部１ａに衝
突するので、該前縁部１ａが最も激しく摩耗す
る。破線は摩耗前の前縁部１ａの形状、実線は摩
耗後の前縁部１ａの形状をそれぞれ示す。そし
て、前縁部１ａの摩耗により、翼形状がくずれる
とフアンの流体性能が低下し、プラントの運転に
重大な支障をきたすことになるので、前縁部１ａ
の耐摩耗性を向上させ、寿命を延ばす必要があ
る。また、経年的に摩耗した場合の保守性も重要
な問題となる。
An exhaust fan in a coal-fired power plant handles combustion exhaust gas from a boiler that includes a fly ash, so the fly ash causes abrasion in the flow path, and particularly severe wear in the rotor blades that rotate at high speed. The wear condition of the rotor blades will be explained with reference to FIGS. 1 and 2, taking the rotor blades of an axial flow fan as an example. Figure 1 is a side view of the rotor blade, and Figure 2 is a sectional view taken along the - arrow in Figure 1.The fly ash in the gas flowing in the direction of the arrow collides with the leading edge 1a of the rotor blade base 1 at high speed. , the leading edge 1a wears most severely. The broken line shows the shape of the leading edge 1a before wear, and the solid line shows the shape of the front edge 1a after wear. If the blade shape collapses due to wear of the leading edge 1a, the fluid performance of the fan will deteriorate and this will seriously impede plant operation.
It is necessary to improve the wear resistance and extend the life of the product. Furthermore, maintainability in the event of wear over time also becomes an important issue.
前記の前縁部１ａの耐摩耗性を向上させるため
には、該前縁部１ａの硬度を上げることが有効で
あり、従来より種々の方法が講じられている。 In order to improve the wear resistance of the leading edge portion 1a, it is effective to increase the hardness of the leading edge portion 1a, and various methods have been conventionally used.
即ち、従来の耐摩耗性動翼においては、第３図
に示したように動翼母体（一般に鋳鋼で作られ
る）１の前縁部１ａに硬質金属２を多重肉盛溶接
した後に、翼形状に仕上成形したり、第４図に示
すように予め硬質金属で成形した前縁部１′ａを
動翼母体１に溶接等で接着したり、あるいは第５
図に示すように予め硬質合金で前縁部１′ａを成
形しておき、動翼母体１を鋳造する時に一緒に鋳
込んで仕上げたりしている。尚、第５図の例で
は、接着強度を向上させるために前縁部１′ａ側
に突起３を設けている。 That is, in the conventional wear-resistant rotor blade, as shown in FIG. 3, after multiple overlay welding of hard metal 2 to the leading edge 1a of the rotor blade base body (generally made of cast steel) 1, the blade shape is As shown in FIG.
As shown in the figure, a leading edge portion 1'a is formed in advance from a hard metal, and is finished by being cast together with the rotor blade base body 1 when it is cast. In the example shown in FIG. 5, a protrusion 3 is provided on the front edge 1'a side in order to improve adhesive strength.
しかし、第３図のものは、硬質金属２の肉盛溶
接及びその仕上成形に多大の時間、労力を要する
と共に、翼形状の寸法精度が悪くなる問題があ
る。また、高硬度の肉盛材は、一般に硬質粒子が
軟質素地中に分散した組織をしているため、粒度
の小さいフライアツシユに対しては軟質素地部が
選択的に侵食され、硬質粒子が脱落して前縁部１
ａの耐摩耗性向上の役目を果せなくなる問題もあ
る。 However, the structure shown in FIG. 3 requires a great deal of time and labor for overlay welding of the hard metal 2 and its final forming, and has the problem that the dimensional accuracy of the blade shape deteriorates. In addition, since high-hardness overlay materials generally have a structure in which hard particles are dispersed in a soft base material, the soft base part is selectively eroded against fly ash with small particle size, and the hard particles fall off. leading edge 1
There is also the problem that it cannot fulfill its role of improving the wear resistance of (a).
また、第４図及び第５図のものは、前縁部１′
ａが摩耗した場合、動翼全体を新規に交換する
か、あるいは肉盛による補修等が必要であり、翼
全体を交換するのはコスト的にきわめて不利とな
り、また肉盛補修は第３図のものと同様に労力、
仕上精度の点で問題がある。 In addition, in the case of FIGS. 4 and 5, the front edge 1'
If a is worn out, the entire rotor blade must be replaced with a new one or repaired by overlaying.Replacing the entire blade is extremely disadvantageous in terms of cost, and overlay repair is shown in Figure 3. labor as well as things,
There is a problem with finishing accuracy.
本発明の目的は、従来よりも耐アツシユエロー
ジヨン性に優れて摩耗寿命の延長を図れると共
に、摩耗した際の補修を簡単に行える耐摩耗動翼
を提供することにある。
An object of the present invention is to provide a wear-resistant rotor blade that has better attachment erosion resistance than conventional blades, can extend its wear life, and can be easily repaired when worn.
この目的を達成するために、本発明の耐摩耗動
翼は、動翼母体の前縁部に、該前縁部の先端部分
を残した切欠きを設けると共に、該切欠部に、セ
ラミツクなどの硬質材で成形され、かつ切欠いた
前縁部の形状と等しい外郭形状をなした前縁部材
を設け、前記前縁部材は動翼母体の長手方向にお
いて複数個に分割されていると共に、該前縁部材
の背面と前記切欠きの前縁部材取付面との間に動
翼母体の根元側から先端側に沿つて形成した凹凸
の嵌合により動翼母体に取付けられて、動翼母体
の根元側から着脱可能となされ、動翼母体の根元
部には前記前縁部材の抜け止めを設けたことを特
徴とする。
In order to achieve this objective, the wear-resistant rotor blade of the present invention is provided with a notch in the leading edge of the rotor blade base, leaving the tip of the leading edge, and in which the notch is made of ceramic or the like. A leading edge member is formed of a hard material and has an outer shape identical to the shape of the notched leading edge, and the leading edge member is divided into a plurality of parts in the longitudinal direction of the rotor blade base. The grooves formed between the back surface of the edge member and the leading edge member mounting surface of the notch from the root side to the tip side of the rotor blade base are fitted to the rotor blade base, and the blade base is attached to the base of the rotor blade. It is characterized in that it can be attached and detached from the side, and that a stopper for the leading edge member is provided at the base of the rotor blade base.
以下、本発明の一実施例を第６図ないし第１１
図により説明する。第６図は本発明による耐摩耗
動翼を示す側面図、第７図は第６図の−矢視
断面図、第８図は第７図における前縁部材を動翼
母体に組付ける前の状態を示す断面図、第９図は
第６図における動翼前縁部の先端部の断面図、第
１０図は前縁部材の抜け止めの一例を示す断面
図、第１１図は第１０図の底面図、第１２図は抜
け止めの他の例を示す断面図、第１３図は第１２
図の底面図を示している。
An embodiment of the present invention will be described below with reference to FIGS. 6 to 11.
This will be explained using figures. FIG. 6 is a side view showing the wear-resistant rotor blade according to the present invention, FIG. 7 is a sectional view taken along the - arrow in FIG. 6, and FIG. 8 is a view of the leading edge member in FIG. 9 is a sectional view of the tip of the leading edge of the rotor blade in FIG. 6, FIG. 10 is a sectional view showing an example of preventing the leading edge member from coming off, and FIG. 11 is as shown in FIG. 10. 12 is a sectional view showing another example of the retainer, and FIG. 13 is a bottom view of the 12th
Figure shows a bottom view.
本発明による耐摩耗動翼は、その動翼母体１の
前縁部に、該前縁部の先端部１ｂを残した切欠き
３を設け、該切欠き３に、セラミツクなどの硬質
材で形成され、かつ切欠いた前縁部の形状と等し
い外郭形状をなした前縁部材４を設けている。前
記前縁部材４は、動翼母体１の長手方向において
複数個（図示では９個）に分割されていて、各分
割前縁部材４ａは、その背面に設けた突起５を、
前記切欠き３の前縁部材取付面に動翼母体１の長
手方向に沿つて形成した逆くさびの溝６に嵌合す
ることにより動翼母体１に取付けられている。つ
まり、各分割前縁部材４ａの突起５を動翼母体１
の根元側から前記溝６に順次嵌合して先端側に向
つてスライドさせることにより、各分割前縁部材
４ａは動翼母体１に取付けられている。また各分
割前縁部材４ａの端面４ｂはストレートに加工さ
れていて、隣接前縁部材４ａ間に隙間が生じない
ようにしてある。 In the wear-resistant rotor blade according to the present invention, a notch 3 is provided at the leading edge of the rotor blade base 1, leaving the tip 1b of the leading edge, and the notch 3 is made of a hard material such as ceramic. A front edge member 4 is provided which has an outer shape that is the same as the shape of the notched front edge. The leading edge member 4 is divided into a plurality of pieces (nine pieces in the illustration) in the longitudinal direction of the rotor blade base 1, and each divided leading edge member 4a has a protrusion 5 provided on its back surface.
It is attached to the rotor blade base 1 by fitting into an inverted wedge groove 6 formed along the longitudinal direction of the rotor blade base 1 on the leading edge member attachment surface of the notch 3 . In other words, the protrusion 5 of each divided leading edge member 4a is connected to the rotor blade matrix 1.
Each divided leading edge member 4a is attached to the rotor blade base 1 by sequentially fitting into the groove 6 from the root side and sliding it toward the tip side. Further, the end surfaces 4b of each divided leading edge member 4a are processed to be straight so that no gap is created between adjacent leading edge members 4a.
一方、動翼母体１の根元部には、前記前縁部材
４の抜き止めが設けられている。この抜け止め
は、第１０図及び第１１図で示したように動翼母
体１の根元部端面１ｃ側からコマ７をねじ込み、
該コマ７を最下段の分割前縁部材４ａと係合させ
た構造か、または第１２図及び第１３図で示した
ように動翼母体１の根元部端面１ｃ側から皿ビス
８をねじ込み、該皿ビス８を最下段の分割前縁部
材４ａと係合させた構造となつている。 On the other hand, a stopper for the leading edge member 4 is provided at the root portion of the rotor blade base 1 . This retainer is achieved by screwing in the piece 7 from the root end surface 1c side of the rotor blade base 1, as shown in FIGS. 10 and 11.
A structure in which the piece 7 is engaged with the lowermost divided leading edge member 4a, or a countersunk screw 8 is screwed in from the root end surface 1c side of the rotor blade base body 1 as shown in FIGS. 12 and 13, The structure is such that the countersunk screw 8 is engaged with the lowermost divided front edge member 4a.
従つて、軸流フアンの運転時、即ち動翼が回転
している時は、遠心力による前縁部材４の抜け出
しは動翼母体１の前縁先端部１ｂにより阻止さ
れ、また動翼の回転停止時における自重による前
縁部材４の抜け出しは前記抜け止めにより阻止さ
れる。 Therefore, when the axial fan is in operation, that is, when the rotor blades are rotating, the leading edge member 4 is prevented from coming off due to centrifugal force by the leading edge tip 1b of the rotor blade base body 1, and the rotation of the rotor blades is prevented. The leading edge member 4 is prevented from coming off due to its own weight when stopped by the stopper.
また、動翼母体１の前縁先端部１ｂには、その
耐摩耗策として、第９図に示すように、ステライ
トなどの硬化肉盛９を施してある。この硬化肉盛
は領域的に小さいので、その肉盛及び仕上作業に
あまり労力を必要としない。 Further, as a wear-resistant measure, a hard overlay 9 made of stellite or the like is applied to the leading edge tip portion 1b of the rotor blade base body 1, as shown in FIG. Since this hardfacing is small in area, it does not require much effort to build up and finish.
しかるに本発明による耐摩耗動翼においては、
最も摩耗の激しい前縁部が、高硬度で耐アツシユ
エロージヨン性の優れた前縁部材４にて構成され
ているので、摩耗寿命が延長される。また前記前
縁部材４が、凹凸の嵌合により動翼母体１に取付
けられた構造となつているので、取付作業の労力
を大幅に改善できる。さらに前縁部材４は複数個
に分割されていると共に、抜け止めのコマ７また
は皿ビス８を外すことにより取外せるようになつ
ているので、摩耗した分割前縁部材４ａのみを新
しいものと交換し、摩耗の軽微なものはそのまゝ
使用することができ、保守の労力、コストを大幅
に改善できる。 However, in the wear-resistant rotor blade according to the present invention,
Since the leading edge, which is subject to the most wear, is constituted by the leading edge member 4 which is highly hard and has excellent resistance to erosion, the wear life is extended. Furthermore, since the leading edge member 4 is attached to the rotor blade base body 1 by fitting the concave and convex portions, the labor required for attachment work can be significantly reduced. Furthermore, the leading edge member 4 is divided into a plurality of parts and can be removed by removing the locking piece 7 or countersunk screw 8, so only the worn divided leading edge member 4a can be replaced with a new one. However, those with slight wear can be used as is, and maintenance labor and costs can be significantly improved.
以上説明したように、本発明によれば、従来よ
りも耐アツシユエロージヨン性に優れて摩耗寿命
の延長を図れると共に、摩耗した際の補修を簡単
に行える効果がある。
As explained above, according to the present invention, it is possible to extend the wear life by having superior attachment erosion resistance than before, and also to be able to easily repair the wear when it wears out.
第１図は軸流フアンの動翼の前縁部が摩耗した
状況を示す側面図、第２図は第１図の−矢視
断面図、第３図ないし第５図は従来の耐摩耗動翼
における前縁部分を示す断面図、第６図ないし第
１３図は本発明の一実施例を示し、第６図は本発
明による耐摩耗動翼の側面図、第７図は第６図の
−矢視断面図、第８図は第７図における前縁
部材を動翼母体に組付ける前の状態を示す断面
図、第９図は第６図における動翼前縁部の先端部
の断面図、第１０図は前縁部材の抜け止めの一例
を示す断面図、第１１図は第１０図の底面図、第
１２図は抜け止めの他の例を示す断面図、第１３
図は第１２図の底面図である。
１……動翼母体、１ａ……動翼の前縁先端部、
３……切欠き、４……前縁部材、４ａ……分割前
縁部材、５……突起、６……溝、７……抜け止め
用のコマ、８……抜け止め用の皿ビス。
Figure 1 is a side view showing the state in which the leading edge of the rotor blade of an axial flow fan is worn out, Figure 2 is a sectional view taken along the - arrow in Figure 1, and Figures 3 to 5 are conventional wear-resistant rotor blades. 6 to 13 show an embodiment of the present invention, FIG. 6 is a side view of the wear-resistant rotor blade according to the present invention, and FIG. 7 is a cross-sectional view showing the leading edge portion of the blade. - A cross-sectional view in the direction of the arrows, FIG. 8 is a cross-sectional view showing the leading edge member in FIG. 7 before being assembled to the rotor blade base, and FIG. 9 is a cross-sectional view of the tip of the leading edge of the rotor blade in FIG. 6. 10 is a cross-sectional view showing an example of a retainer for the front edge member, FIG. 11 is a bottom view of FIG. 10, FIG. 12 is a cross-sectional view showing another example of a retainer, and FIG.
The figure is a bottom view of FIG. 12. 1... Moving blade matrix, 1a... Leading edge tip of moving blade,
3... Notch, 4... Front edge member, 4a... Divided front edge member, 5... Protrusion, 6... Groove, 7... Piece for retaining, 8... Flat screw for retaining.
Claims (1)
アンの耐摩耗動翼であつて、動翼母体の前縁部
に、該前縁部の先端部分を残した切欠きを設ける
と共に、該切欠部に、セラミツクなどの硬質材で
成形され、かつ切欠いた前縁部の形状と等しい外
郭形状をなした前縁部材を設け、前記前縁部材は
動翼母体の長手方向において複数個に分割されて
いると共に、該前縁部材の背面と前記切欠きの前
縁部材取付面との間に動翼母体の根元側から先端
側に沿つて形成した凹凸の嵌合により動翼母体に
取付けられて、動翼母体の根元側から着脱可能と
なされ、動翼母体の根元部には前記前縁部材の抜
け止めを設けたことを特徴とする耐摩耗動翼。1. A wear-resistant rotor blade for an axial flow fan that handles gas containing abrasive particles, in which a notch is provided at the leading edge of the rotor blade matrix, leaving the tip of the leading edge, and the notch is A leading edge member formed of a hard material such as ceramic and having an outer shape equal to the shape of the notched leading edge is provided in the part, and the leading edge member is divided into a plurality of parts in the longitudinal direction of the rotor blade base. At the same time, the blade is attached to the rotor blade base by fitting the unevenness formed along the root side to the tip side of the rotor blade base between the back surface of the leading edge member and the leading edge member mounting surface of the notch. 1. A wear-resistant rotor blade, characterized in that the rotor blade is detachable from the root side of the rotor blade base, and a stopper for the leading edge member is provided at the root of the rotor blade base.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9065583A JPS59215905A (en) | 1983-05-25 | 1983-05-25 | Wear resistant bucket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9065583A JPS59215905A (en) | 1983-05-25 | 1983-05-25 | Wear resistant bucket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS59215905A JPS59215905A (en) | 1984-12-05 |
| JPS6240525B2 true JPS6240525B2 (en) | 1987-08-28 |
Family
ID=14004534
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP9065583A Granted JPS59215905A (en) | 1983-05-25 | 1983-05-25 | Wear resistant bucket |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS59215905A (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2198667B (en) * | 1986-12-20 | 1991-08-07 | Refurbished Turbine Components | Parts for and methods of repairing machines |
| US5358379A (en) * | 1993-10-27 | 1994-10-25 | Westinghouse Electric Corporation | Gas turbine vane |
| US5531570A (en) * | 1995-03-06 | 1996-07-02 | General Electric Company | Distortion control for laser shock peened gas turbine engine compressor blade edges |
| DE19617556A1 (en) * | 1996-05-02 | 1997-11-06 | Asea Brown Boveri | Thermally loaded blade for a turbomachine |
| US5791874A (en) * | 1997-01-23 | 1998-08-11 | Brunswick Corporation | Marine propeller with adjustable cupping |
| DE102005061673A1 (en) * | 2005-12-21 | 2007-07-05 | Rolls-Royce Deutschland Ltd & Co Kg | Leading edge formation for the compressor blades of gas turbine engines |
| US7762783B2 (en) * | 2007-01-11 | 2010-07-27 | General Electric Company | Turbine blade apparatus |
| JP5614131B2 (en) * | 2010-07-01 | 2014-10-29 | 株式会社Ihi | Fan blade and fan |
| US10323521B2 (en) | 2013-03-15 | 2019-06-18 | United Technologies Corporation | Hybrid fan blade biscuit construction |
| EP2971527B1 (en) * | 2013-03-15 | 2020-08-05 | United Technologies Corporation | Hybrid fan blade biscuit construction |
| FR3010132A1 (en) * | 2013-09-04 | 2015-03-06 | Safran | WAVE METAL ATTACK EDGE IN COMPOSITE MATERIAL FOR GAS TURBINE ENGINE |
| CN112901279B (en) * | 2021-01-29 | 2022-03-29 | 大连理工大学 | Turbine blade adopting bolt-fixed ceramic armor |
-
1983
- 1983-05-25 JP JP9065583A patent/JPS59215905A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS59215905A (en) | 1984-12-05 |
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