WO2015050013A1 - タービンブレード用予備成形体及びタービンブレードの製造方法 - Google Patents

タービンブレード用予備成形体及びタービンブレードの製造方法 Download PDF

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Publication number
WO2015050013A1
WO2015050013A1 PCT/JP2014/075068 JP2014075068W WO2015050013A1 WO 2015050013 A1 WO2015050013 A1 WO 2015050013A1 JP 2014075068 W JP2014075068 W JP 2014075068W WO 2015050013 A1 WO2015050013 A1 WO 2015050013A1
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WO
WIPO (PCT)
Prior art keywords
turbine blade
preform
hot forging
main body
blade
Prior art date
Application number
PCT/JP2014/075068
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
佳祐 青山
尚史 光永
松本　英樹
Original Assignee
日立金属株式会社
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 日立金属株式会社 filed Critical 日立金属株式会社
Priority to JP2015540454A priority Critical patent/JP6206739B2/ja
Priority to CN201480003415.2A priority patent/CN104870120A/zh
Publication of WO2015050013A1 publication Critical patent/WO2015050013A1/ja

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
    • B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
    • B21K3/04—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like blades, e.g. for turbines; Upsetting of blade roots
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J13/00—Details of machines for forging, pressing, or hammering
    • B21J13/02—Dies or mountings therefor

Definitions

  • the present invention relates to a turbine blade preform and a turbine blade manufacturing method used when manufacturing a turbine blade material by hot forging.
  • the die is forged while maintaining the horizontal state from the blade root to the blade tip, and after the die forging is completed, the turbine blade is subjected to the necessary torsion processing, subjected to forced restraint correction in such a state, and then heat-treated in the restrained state.
  • a method for manufacturing a large turbine blade There is an invention of a method for manufacturing a large turbine blade. Further, as an invention focusing on a preform for a turbine blade, for example, a simple material as disclosed in Japanese Patent Publication No. 3-136 (Patent Document 2) is used, and a wing portion is formed by a die. On the other hand, there is an invention of a method for forming a preform for a turbine blade in which a blade root portion is formed by front-rear extrusion into a closed mold and further a flange portion is formed by upsetting.
  • JP 63-241118 A Japanese Patent Publication No. 3-136
  • Patent Document 1 The method described in Patent Document 1 described above is not economical because a special process called twisting is required and the number of processes increases. If the blade material is to be obtained efficiently by hot forging, it is advantageous to perform hot forging using a near net-shaped mold.
  • the turbine blade preform as disclosed in Patent Document 2 there is no means for positioning when the turbine blade preform is placed on the mold, so a near-net mold is used. If hot forging is performed, there is a possibility that a position shift occurs and a defect such as a lack of wall occurs.
  • An object of the present invention is to provide a turbine blade preform and a method for manufacturing a turbine blade that can easily position a mold even when a large hot forging machine is used.
  • the present invention is a turbine blade preform that is a hot-forged turbine blade material having a blade portion and a root portion, and the turbine blade preform is a portion that is forged into a blade portion.
  • the turbine blade preform is provided with a main body part integrally formed with the root part, and projecting parts protruding in the axial direction at both ends in the axial direction of the main body part.
  • the said projection part is joined to the said main-body part.
  • the projections are joined by fitting with screws and / or welding.
  • the material of the main body is a Ti alloy.
  • the present invention also relates to a method for producing a turbine blade material having a blade portion and a root portion by arranging a preform for a turbine blade in a hot forging die, performing hot forging, and for the turbine blade.
  • the pre-formed body is formed by integrally forming a portion that becomes a wing portion and a portion that becomes a wing portion by hot forging, and a main body portion having portions having different thicknesses in the axial direction, and both end portions in the axial direction.
  • the hot forging die has an upper die and a lower die, and a die engraved surface forming a blade portion and a root portion of the turbine blade is formed
  • the lower mold has a positioning groove in which the protrusion is disposed when the turbine blade preform is disposed.
  • the protrusion is disposed in the positioning groove, and the turbine blade preform is disposed in the lower mold. Place on the mold and press the upper mold It is a manufacturing method of a turbine blade to perform more hot forging.
  • the material of the main body is preferably a Ti alloy.
  • the positioning portions for determining the hot forging position are formed at both locations that are the longitudinal axes of the main body of the preform, There is no possibility that the molded body will be displaced. Therefore, when hot forging is performed using the turbine blade preform of the present invention, defects such as undercutting can be prevented, the weight of the preform can be reduced, and the yield can be improved.
  • FIG. 1 is a schematic view of a turbine blade preform 1 showing an example of the present invention.
  • the turbine blade preform 1 is formed by integrally forming a portion that becomes a wing portion and a portion that becomes a root portion by hot forging, and a main body portion 2 having portions having different diameters in the axial direction. Projections 3 projecting in the axial direction are formed at both ends.
  • the axial direction means the direction of the central axis of the turbine blade preform 1 as shown in FIG.
  • the part from which thickness differs in an axial direction is a place where the diameter is changing in order to shape
  • Protrusions 3 projecting in the axial direction are formed at both ends in the axial direction.
  • the protrusion 3 is installed in a positioning groove 5 provided in the lower mold 4 shown in FIG.
  • the positioning groove 5 is provided in advance at a location where a defect such as a lacking wall is not generated by hot forging.
  • the projection 3 is used to place the turbine blade preform 1 in a predetermined position before hot forging, and the turbine blade preform 1 is displaced in the hot forging die during hot forging. To prevent it.
  • the protrusions are indispensable for placing in a desired position of the hot forging die and performing hot forging in order from the desired pressing place at the time of hot forging.
  • the formation of the above-described protrusion is joined to the main body as a component different from the main body.
  • the protrusion of the present invention functions as a “positioning member”. Therefore, it is important to provide a protrusion at a predetermined location. For example, if it is attempted to form the main body portion and the protruding portion as a single body by hot working such as hot forging, the possibility that the protruding portion is detached from a desired position of the main body portion is increased. On the other hand, if it joins to a main-body part as another component, a projection part can be reliably joined to a desired position.
  • the position which joins the projection part of another component to a main-body part should just be a center position of the main body part of the surface side which a projection part joins.
  • it is good to join on the central axis of a main-body part.
  • the material of the protrusion is preferably the same as that of the main body. This is because when the protrusion is removed together with the burr from the turbine blade material after hot forging, it can be reused as a recycling material together with the burr.
  • a method of joining the protrusions it is easy to fit them by screws or / or by welding.
  • the dimension of a projection part should just be a cylindrical thing with a diameter of 40 mm or more.
  • the reason for the columnar shape is that it can be easily placed in the positioning groove formed in the hot forging die.
  • the diameter of the protrusion is preferably 40 mm or more.
  • the upper limit of the diameter of the protrusion is not particularly limited, but it is sufficient if it is 50 mm or less.
  • the main body of the present invention described above is preferably a Ti alloy. Since turbine blades made of Ti alloy are expected to become longer blades and larger in the future, it is preferable to apply the preform for a turbine blade of the present invention.
  • the hot forging referred to in the present invention includes hot pressing, hot die forging, and isothermal forging.
  • a method for manufacturing a turbine blade of the present invention will be described with reference to examples.
  • the two materials are Ti alloys.
  • the 50-inch class turbine blade preform 1 has a shape in which the cross-sectional shape of the main body portion 2 is circular, and the volume is changed in order to form the blade portion and the root portion.
  • the cross-sectional shape is circular.
  • the cross-section may be rectangular.
  • One of the turbine blade preforms was threaded on the blade-side end surface and the root-side end surface on the extension line of the central axis of the main body 1.
  • the cylindrical Ti alloy projecting portion 3 having a diameter of 40 mm as the projecting portion is also threaded, the main body portion and the projecting portion are screwed, and further welded, so that the main body portion 2 and the projecting portion are formed.
  • the part 3 was joined to form a turbine blade preform 1.
  • the Ti alloy of the protrusion and the Ti alloy of the main body have the same composition.
  • the remaining one of the turbine blade preforms is a cylindrical projection having a diameter of 40 mm by grinding the blade-side end surface and the root-side end surface on the extension line of the central axis of the main body 1.
  • the Ti alloy for use was joined to the main body portion 2 by friction welding to form a preform 1 for a turbine blade having a protrusion on the extension line of the central axis of the main body portion 1.
  • the one using the friction welding can omit the screw machining step and reduce man-hours. Note that the Ti alloy of the protrusion and the Ti alloy of the body have the same composition.
  • hot forging dies (upper die and lower die) were prepared.
  • a hot-forged die blade and a die-carved surface forming a root were used.
  • the lower mold 4 has a positioning groove 5 in which the projection 3 is disposed when the turbine blade preform 1 is disposed. It was.
  • the turbine blade preform is coated with a lubricant, heated to a forging temperature of 940 ° C., and the projection 3 of the turbine blade preform 1 is disposed in the positioning groove 5.
  • the preform 1 was placed on the lower mold 4. The state after arrangement was as shown in FIG.
  • Hot forging was performed with one blow by pressing an upper die (not shown). Hot forging was started from a turbine blade preform in which the main body and the protrusion were screwed, followed by a turbine blade preform in which the main body and the protrusion were friction welded.
  • the hot forging machine used is a large hot forging machine with a maximum load of 50,000 tons. Projections were observed during hot forging, but there was no evidence of misalignment of the turbine blade preform during hot forging, and a turbine blade material with a desired shape could be obtained. did it.
  • the preform is displaced during forging.
  • defects such as lacking can be prevented.
  • the weight of the preform can be reduced and the yield can be improved.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Forging (AREA)
PCT/JP2014/075068 2013-10-01 2014-09-22 タービンブレード用予備成形体及びタービンブレードの製造方法 WO2015050013A1 (ja)

Priority Applications (2)

Application Number Priority Date Filing Date Title
JP2015540454A JP6206739B2 (ja) 2013-10-01 2014-09-22 タービンブレードの製造方法
CN201480003415.2A CN104870120A (zh) 2013-10-01 2014-09-22 涡轮叶片用预成型体和涡轮叶片的制造方法

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2013-206291 2013-10-01
JP2013206291 2013-10-01

Publications (1)

Publication Number Publication Date
WO2015050013A1 true WO2015050013A1 (ja) 2015-04-09

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Country Status (3)

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JP (1) JP6206739B2 (zh)
CN (1) CN104870120A (zh)
WO (1) WO2015050013A1 (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2018051586A (ja) * 2016-09-28 2018-04-05 日立金属株式会社 タービンブレード用素材の製造方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106513479B (zh) * 2016-11-04 2018-08-14 贵州航飞精密制造有限公司 一种涡轮叶片的弯曲加工工艺方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB760132A (en) * 1953-12-22 1956-10-31 Rolls Royce Improvements relating to forging methods and apparatus therefor
JPH0446651A (ja) * 1990-06-12 1992-02-17 Agency Of Ind Science & Technol タービン翼の製造方法
JPH08189303A (ja) * 1994-09-07 1996-07-23 Soc Natl Etud Constr Mot Aviat <Snecma> ターボエンジンの中空羽根の製造方法

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB760132A (en) * 1953-12-22 1956-10-31 Rolls Royce Improvements relating to forging methods and apparatus therefor
JPH0446651A (ja) * 1990-06-12 1992-02-17 Agency Of Ind Science & Technol タービン翼の製造方法
JPH08189303A (ja) * 1994-09-07 1996-07-23 Soc Natl Etud Constr Mot Aviat <Snecma> ターボエンジンの中空羽根の製造方法

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2018051586A (ja) * 2016-09-28 2018-04-05 日立金属株式会社 タービンブレード用素材の製造方法

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JP6206739B2 (ja) 2017-10-04
CN104870120A (zh) 2015-08-26
JPWO2015050013A1 (ja) 2017-03-09

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