EP3281719A1 - Matrice de forgeage à chaud et procédé de forgeage à chaud - Google Patents

Matrice de forgeage à chaud et procédé de forgeage à chaud Download PDF

Info

Publication number
EP3281719A1
EP3281719A1 EP16776474.5A EP16776474A EP3281719A1 EP 3281719 A1 EP3281719 A1 EP 3281719A1 EP 16776474 A EP16776474 A EP 16776474A EP 3281719 A1 EP3281719 A1 EP 3281719A1
Authority
EP
European Patent Office
Prior art keywords
forging
hot
hot forging
forging material
die
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.)
Granted
Application number
EP16776474.5A
Other languages
German (de)
English (en)
Other versions
EP3281719B1 (fr
EP3281719A4 (fr
Inventor
Hisashi MITSUNAGA
Tsuyoshi Fukui
Toshiya Teramae
Toshiaki Nonomura
Hideki Matsumoto
Eiji SHIMOHIRA
Satoshi KOHIKI
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Proterial Ltd
Original Assignee
Hitachi Metals Ltd
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 Hitachi Metals Ltd filed Critical Hitachi Metals Ltd
Publication of EP3281719A1 publication Critical patent/EP3281719A1/fr
Publication of EP3281719A4 publication Critical patent/EP3281719A4/fr
Application granted granted Critical
Publication of EP3281719B1 publication Critical patent/EP3281719B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • B21J1/00—Preparing metal stock or similar ancillary operations prior, during or post forging, e.g. heating or cooling
    • B21J1/04—Shaping in the rough solely by forging or pressing
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J7/00—Hammers; Forging machines with hammers or die jaws acting by impact
    • B21J7/02—Special design or construction
    • B21J7/14—Forging machines working with several hammers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J9/00—Forging presses
    • B21J9/02—Special design or construction
    • B21J9/06—Swaging presses; Upsetting presses

Definitions

  • the present invention relates to a hot forging die and a hot forging method.
  • a hot forging material having a round rod shape is stretched to a desired diameter, and a preform having a desired round rod shape in which the volume of a portion for forming a root portion or a wing portion of a turbine blade is secured is formed by closed die forging such that a turbine blade material having a near net shape is obtained.
  • Fig. 2 of JP-A-63-238942 shows a preform having a shape in which a portion for forming a root portion is thick (the volume is high) and is gradually tapered toward a tip of a wing portion.
  • a specific manufacturing method of the preform includes: radially forging a hot forging material having a round rod shape to obtain a long round bar material having a desired diameter; cutting the long round bar material in a predetermined dimension; and forging the cut round bar material into a desired preform shape using a separate open die forging machine.
  • a portion for forming a root portion or a wing portion, or a protrusion called a boss portion may be provided in a wing portion of the turbine blade.
  • a preform does not sufficiently fulfills in a die face during closed die forging. Therefore, there is a problem in that a part of a turbine blade material having a near net shape is deficient after closed die forging.
  • a material of a turbine blade is an expensive alloy such as a Ni-based superalloy or a Ti alloy. Therefore, in a case where a problem, such as deficiency of a part of a turbine blade material having a near net shape after closed die forging, occurs, the damage is significant.
  • a processing groove may be sequentially formed by necking in a material having a round rod shape using a special jig in a press machine.
  • a pressing portion of the jig is formed flat to have the same width. Therefore, the jig is not suitable for forming a desired groove in a difficult-to-work material. Further, a groove formed by necking has a small width and is vertically deep. In a case where a groove is formed in a direction perpendicular to a depth direction of a forging material, there is a problem in that an overlap defect occurs during hot forging in which the forging material is stretched to the length of a turbine blade.
  • An object of the present invention is to provide a hot forging die and a hot forging method, in which even a difficult-to-work material used for a turbine blade can be easily necked using a radial forging machine.
  • the present invention has been made in consideration of the above-described circumstances.
  • a hot forging die for hot-forging a rod-shaped forging material by radial forging
  • the hot forging die including a pair of halved pressing portions for interposing the forging material between the pair of the halved pressing portions, in which each of the halved pressing portions being a convex portion having a substantially semicircular cross-section, the convex portion being continuous so as to surround the forging material, and each of the halved pressing portions includes a rough processing portion and a finishing portion being a convex portion having a larger curvature radius than the rough processing portion.
  • each of the halved pressing portions includes a gradual change portion in which a curvature radius of the halved pressing portion gradually increases in a direction from the rough processing portion to the finishing portion.
  • a curvature radius of the convex portion having a substantially semicircular shapein the finishing portion is larger than a curvature radius of a convex portion having a substantially semicircular shape in the rough processing portion by 10 mm or more.
  • each of the halved pressing portions has a pressing portion for necking.
  • a plurality of the pressing portions for necking are provided in a longitudinal direction of the forging material.
  • a hot forging method for hot-forging a rod-shaped forging material by radial forging by using hot forging die comprising a pair of halved pressing portions for interposing the forging material between the pair of the halved pressing portions, each of the halved pressing portions being a convex portion having a substantially semicircular cross-section, the convex portion being continuous so as to surround the forging material, each of the halved pressing portions including a rough processing portion and a finishing portion being a convex portion having a larger curvature radius than the rough processing portion.
  • the hot forging method includes:
  • the rod-shaped forging material is formed of a Ni-based heat-resistant superalloy or a Ti alloy.
  • the hot forging method according to the present invention is suitable for manufacturing a preform for a turbine blade.
  • an object for necking is a small product called a connecting rod.
  • a material thereof is a Ni-based heat-resistant superalloy or a Ti alloy which is known as a difficult-to-work material.
  • some of the alloys have a small temperature range where hot forging is possible. Therefore, the temperature of a forging material which is formed of this alloy decreases during open die forging in which a jig for necking is used. Therefore, although dependent on the weight of a forging material, for example, a forging material for a 40 to 60-inch turbine blade is required to be reheated seven to ten times. As the size of a turbine blade increases, the number of times of reheating increases.
  • the present invention can solve this problem, and the greatest feature thereof is a novel shape which is applicable to formation of a preform for a large turbine blade using a radial forging machine.
  • a hot forging die used in the present invention will be described.
  • Fig. 1 shows a schematic side view showing a hot forging die 1 according to the present invention, a cross-sectional view (cross-sectional view A-A) showing a finishing portion of the hot forging die 1, a cross-sectional view (cross-sectional view C-C) showing a rough processing portion of the hot forging die 1, and a cross-sectional view (cross-sectional view B-B) showing a space between the finishing portion and the rough processing portion.
  • a radial forging machine that presses a forging material in two directions opposite to each other is used.
  • the curvature radius of each of the halved pressing portions shown in the cross-sectional views gradually increases.
  • the curvature radius is substantially the same.
  • the finishing portion described in the present invention refers to a portion having the same curvature radius which includes the position (bottom) shown in the cross-sectional view A-A.
  • Two hot forging dies 1 shown in Fig. 1 are set as a pair.
  • the two hot forging dies are facing each other such that a forging material 21 is interposed therebetween, and the pair of two hot forging dies 1 cooperate together for necking.
  • the two hot forging dies 1 shown in Fig. 1 are set as a pair, and include halved pressing portions 2 between which the forging material (not shown in Fig. 1 ) is interposed.
  • the forging material is interposed between the halved pressing portions and pressed.
  • the forging material is held and intermittently rotated by a holding mechanism included in a radial forging machine.
  • each of the halved pressing portions 2 has a convex portion having a substantially semicircular cross-section which is continuous so as to surround the forging material. Since the pressing portions are halved, the forging material can be interposed between the pressing portions of the two hot forging dies that cooperate together.
  • the shape which is continuous so as to surround the forging material refers to a shape in which the periphery of the forging material 21 is surrounded by the rough processing portions and the finishing portions as shown in Fig. 4 .
  • the halved pressing portion 2 is formed such that a concave is formed on a flat surface, and the pressing portion has an arc shape when seen from a side of the halved pressing portion 2 (in the schematic side view of Fig. 1 ).
  • the halved pressing portion 2 includes a finishing portion 4 and rough processing portions 3.
  • the finishing portion 4 is formed around the concave (arc-shaped) bottom, and the rough processing portions 3 are formed on each of both sides (both end sides of the concave (arc-shaped) portion) of the finishing portion.
  • the distance between the rough processing portions increases in a direction from the bottom of the finishing portion 4 to the end portions of the opposite rough processing portions 3.
  • the forging material When the two hot forging dies press the forging material, the forging material can be pressed in a continuous substantially semicircular convex shape.
  • the convex rough processing portions formed in the hot forging die comes into contact with the forging material first such that a necessary groove can be sequentially formed by necking. Therefore, "the convex portion having a substantially semicircular cross-section" described in the present invention refers to a shape when seen from the direction of the respective cross-sectional views. That is, the cross-section refers to a cross-section when seen from a direction perpendicular to a longitudinal direction of the forging material.
  • each of the halved pressing portions 2 includes the rough processing portion 3 and the finishing portion 4 having a convex portion having a larger curvature radius than the rough processing portion.
  • the reason for this is as follows.
  • the contact area is reduced for effective necking such that a groove having a predetermined depth can be efficiently formed even in a difficult-to-work forging material when the forging of the forging material starts from the rough processing portions.
  • the forging material is sequentially pressed toward the finishing portion such that the width of the groove increases and a necking shape is adjusted.
  • the depth of the groove may not reach a necking depth. Therefore, even in the finishing portion, the contact area is reduced as much as possible by forming a pressing portion having a substantially semicircular cross-section. As a result, the necking shape can be efficiently adjusted.
  • the groove can be efficiently formed by the rough processing portion 3 having a small curvature radius.
  • the groove can be formed in a final shape by the finishing portion 4 having a larger curvature radius than that of the rough processing portion 3. Therefore, a gradual change portion can be formed, in which the curvature radius gradually increases from the substantially semicircular pressing portion formed in the rough processing portion 3 and in which the curvature radius in the convex finishing portion 4 is larger than that of the rough processing portion.
  • a substantially semicircular convex portion may be formed, for example, by build-up welding, and then the shape may be manually machined. Therefore, the formed convex portion does not necessarily have the same curvature radius. Therefore, "the substantially semicircular" described in the present invention only has to be a convex shape having a curvature which has a margin of error generated by build-up welding or machining. The curvature may be obtained from an approximate shape.
  • the portion that presses the forging material only has a convex portion having a curvature, and the curvature of the pressing portion is configured according to the present invention.
  • a curvature radius of a substantially semicircular convex portion in the finishing portion 4 is larger than a curvature radius of a substantially semicircular convex portion in the rough processing portion 3 by 10 mm or more.
  • the reason for this is as follows.
  • the forging material according to the present invention is a preform for a large turbine blade, and in the preform for a large (long) turbine blade, it is preferable that the contact area between the rough processing portion and the finishing portion is large.
  • another reason is that, in a case where the curvature radius of the substantially semicircular convex portion in the finishing portion is large, a processing groove having a wide width can be easily formed.
  • the width of the processing groove formed by necking is large.
  • the curvature radius of a substantially semicircular convex portion in the finishing portion 4 is adjusted to be larger than the curvature radius of the substantially semicircular convex portion in the rough processing portion 3 by 10 mm or more.
  • the difference is preferably 15 mm or more.
  • the hot forging die 1 according to the present invention is suitable for necking.
  • a plurality of halved pressing portions 2 for necking may be formed in the longitudinal direction of the forging material.
  • the reason for this is as follows.
  • an alloy material used for a turbine blade is a difficult-to-work material. Therefore, it is preferable that forging is finished within the shortest possible time in a temperature range where hot forging is possible.
  • the simultaneous formation of a plurality of grooves by necking is effective in a portion for forming a boss portion which is provided in a wing portion of a turbine blade.
  • the simultaneous formation of a plurality of grooves by necking can be realized by using a radial forging machine in combination with the hot forging die according to the present invention in which the contact area of the pressing portion gradually increases from a small area to a large area.
  • the finishing portion is a portion having the same curvature radius which includes a position (bottom) shown in the cross-sectional view E-E (ranging from a position shown in a cross-sectional view F-F to a position shown in a cross-sectional view E-E).
  • a hot forging die 11 used in this case includes a stretching portion 7 that stretches the forging material.
  • a pressing portion for stretching that is provided in the stretching portion 7, as shown in Fig. 3 , the pressing portion is formed flat (flat in the longitudinal direction of the forging material 2 and curved such that the forging material 2 is inserted thereinto).
  • the stretching portion 7 for stretching includes a pair of halved pressing portions 12 between which the forging material is interposed, in which each of the halved pressing portions 12 has a substantially semicircular convex shape which is continuous so as to surround the forging material, and each of the halved pressing portions 12 includes a substantially flat rough processing portion 13 and a finishing portion 14.
  • the basic configuration is the same as that of the hot forging die suitable for necking.
  • two hot forging dies 11 for stretching shown in Fig. 3 are set as a pair.
  • the forging material is held and rotated by a holding mechanism included in a radial forging machine such that the pair of hot forging dies 11 for stretching cooperate together to reduce the diameter of the forging material (not shown).
  • the held forging material moves in the longitudinal direction and is also stretched in the longitudinal direction.
  • the width of the substantially flat pressing portion formed in the rough processing portion 13 is set to be narrow and the width of the pressing portion formed in the finishing portion 14 is set to be wider than that of the rough processing portion 13 such that the contact area is reduced for efficient stretching in the initial stage of forging and then a predetermined shape is obtained.
  • the shape of the hot forging die is adjusted while stretching the forging material in the longitudinal direction. Therefore, the pressing portion becomes flat.
  • the width of the flat pressing portion (the width in the longitudinal direction of the forging material) is excessively wide, a pressure required for forging is large. Therefore, it is preferable that the width of the flat pressing portion is adjusted to be suitable for a forging machine in consideration of the contact area such that the forging material can be efficiently stretched by impacting it once.
  • Fig. 4 is a schematic diagram showing an example of a radial forging machine.
  • the hot forging dies 1 shown in Fig. 1 are attached to the radial forging machine.
  • Each of the hot forging dies 1 are provided on each of opposite surfaces to the forging material such that the forging material 21 is interposed between the hot forging dies 1.
  • the forging material 21 is held in the radial forging machine.
  • the forging material is heated to a predetermined hot forging temperature in a heating furnace (not shown) and is attached to the radial forging machine.
  • the heating temperature varies depending on the material of the forging material. For example, in a case where the material of the forging material is a Ni-based heat-resistant superalloy, the heating temperature is 950°C to 1150°C. In a case where the material of the forging material is a Ti alloy, the heating temperature is 800°C to 1000°C. In addition, in a case where the material of the forging material is a precipitation hardening stainless steel, the heating temperature is 900°C to 1200°C.
  • the shape of the forging material is a rod shape. The rod-shaped forging material only has to be adjusted to a predetermined shape using a forging machine or a press machine. In a case where the forging material has a round rod shape, it is preferable that the diameter of the forging material is the same as the distance of the rough processing portions of the hot forging die 1 for necking.
  • the forging material having a predetermined round rod shape is attached to the radial forging machine.
  • the forging material is necked by rotating the heated forging material 21 and concurrently pressing the forging material using each of the halved pressing portions of the pair of two hot forging dies 1 which are facing each other.
  • the shape of the hot forging die for necking is as shown in Fig. 1 .
  • hot forging starts from the rough processing portions 3 of the hot forging die 1.
  • the hot forging die according to the present invention has a shape in which the distance between the rough processing portions increases in a direction from the finishing portion 4 to the rough processing portions 3 and in which, when the two hot forging dies press the forging material, the forging material can be pressed in a continuous substantially semicircular convex shape.
  • the forging material rotates at the same position (does not move in the longitudinal direction of the forging material).
  • Examples of a necking method include two methods. As a first method, a method in which the shape after completion of necking is emphasized will be described first.
  • predetermined positions of the forging material start to be pressed by the rough processing portions 3 first.
  • Contact (forging) positions between the forging material 21 and the hot forging die during rough processing are indicated by arrows.
  • the forging material is hot-forged in the two directions opposite to each other and, in the initial stage of forging, starts to be pressed by the rough processing portions formed in the two hot forging dies that cooperate together to forge the forging material.
  • the number of positions where the forging material is pressed at the start of forging is four.
  • the contact area is small, and thus a groove can be efficiently formed.
  • the shape of the forging material is adjusted to a predetermined shape in the finishing portions that are formed in the pair of hot forging dies.
  • the number of positions where the forging material 21 is pressed during hot forging in the bottoms of the finishing portions is two. That is, in the initial stage of necking, the four positions are forged (necked) using the pair of hot forging dies. During the adjustment of a final shape, the two positions are forged using the pair of hot forging dies.
  • the shape of the forging material can be adjusted.
  • the forging material can be efficiently formed in a final shape in the finishing portions 4 each having a convex portion having a larger curvature radius than the rough processing portions.
  • the final shape of the forging material can be adjusted to the bottom shape of the finishing portion indicated by an arrow. Therefore, this method is suitable in a case where the final finished shape is emphasized.
  • a second method is a method which is applicable to a case where the processing time is short.
  • predetermined positions of the forging material start to be pressed by the rough processing portions 3 first.
  • Contact (forging) positions between the forging material 21 and the hot forging die during rough processing are indicated by arrows.
  • the forging material is hot-forged in the two directions opposite to each other and, in the initial stage of forging, starts to be pressed by the rough processing portions formed in the two hot forging dies that cooperate together to forge the forging material.
  • the number of positions where the forging material is pressed at the start of forging is four.
  • the contact area is small, and thus a groove can be efficiently formed.
  • the curvature radius is substantially the same. Therefore, finishing is not performed in the bottoms of the finishing portions and can be finished in a state where the number of positions where the hot forging material is pressed during finishing is four as shown in Fig. 7(B) . Even in this case, the forging material can be efficiently formed in a final shape in the convex finishing portion 4 having a larger curvature radius than the rough processing portion. In addition, since the number of positions where the hot forging material is pressed is four, necking can be finished within a short period of time. Thus, this method is suitable in a case where it is desired that the forging time is short.
  • the curvature radius (the curvature radius when seen from a direction perpendicular to the longitudinal direction of the forging material shown in Fig. 7 ) of the bottom (position shown in the cross-sectional view A-A) of the finishing portion to be less than the curvature radius of the diameter after necking.
  • the bottom of the finishing portion is curved in order to avoid excessive stress concentration during hot forging.
  • the hot forging die 1 is replaced with the hot forging die 11 including the pressing portion for stretching.
  • the forging material is reheated to a predetermined forging temperature.
  • the replaced hot forging die 11 includes the stretching portion 7 including the pressing portion for stretching that stretches the forging material.
  • the pressing portion for stretching has a shape shown in Fig. 3 .
  • the shape of the pressing portion is the same as that of the hot forging die 1 for necking shown in Fig. 6(A) . Therefore, in a case where hot forging starts from two directions opposite to each other, predetermined positions of the forging material start to be pressed by the rough processing portions 13 first.
  • the forging material is hot-forged in the two directions opposite to each other and, in the initial stage of stretching (forging), starts to be pressed by the rough processing portions formed in the two (the pair of) hot forging dies that cooperate together to forge the forging material.
  • the number of positions where the forging material is pressed at the start of forging is four.
  • the contact area is small, and thus the forging material can be efficiently stretched.
  • the forging material is sequentially moved in the longitudinal direction of the forging material while being intermittently rotated by the radial forging machine, and then is sequentially hot-forged toward the finishing portions.
  • the shape of the forging material is adjusted to a predetermined shape in the finishing portions that are formed in the pair of hot forging dies.
  • the number of positions where the forging material is pressed during hot forging in the finishing portions 14 is two.
  • the method of adjusting the final shape to the bottom shape of the finishing portion is suitable in a case where the final finished shape is emphasized.
  • the number of positions where the hot forging material is pressed from the initial stage to the final stage of hot forging is adjusted to four as shown in Fig. 7 .
  • the forging material can be stretched within a short period of time.
  • the hot forging die including the pressing portion for stretching can be made to have a shape shown in Fig. 8 .
  • a concave portion 8 is formed in a region from the bottom in the width of the finishing portion 14 (the width in the longitudinal direction of the forging material) to the rough processing portion. Due to the concave portion 8, the pressing portion of the finishing portion is divided into two areas.
  • the forging material can be more reliably prevented from being bent during stretching. In a case where the forging material is hot-forged using the hot forging die shown in Fig.
  • the final stage of forging is performed in the bottom of the finishing portion shown in the cross-sectional view A-A.
  • the forging material When the forging material is pressed, there are two portions including: a pressed portion that is pressed by the finishing portion; and a portion that is not pressed by the finishing portion and is adjacent to the portion pressed by the finishing portion. A part of the pressed portion flows to the non-pressed portion such that the cross-section of the forging material is slightly elliptical. The elliptical forging material is likely to be bent during forging.
  • the pressing portion finishing portion
  • the concave portion is divided by the concave portion.
  • the forging material is intermittently rotated by radial forging in the initial pressing portion and is finished in the next pressing portion.
  • four portions in total are pressed in the structure shown in Fig. 8 . Therefore, as described above, an elliptical shape and a bent shape can be corrected in the pressing portion.
  • the concave portion By forming the concave portion at positions including the bottom of the finishing portion (the position in contact with the straight line A-A in Fig. 8 ), the effect of preventing bending can be exhibited as much as possible.
  • the forging material can be continuously hot-forged into a predetermined preform shape by using the same radial forging machine not only for necking but also for stretching. Therefore, unlike the related art, it is not necessary to perform stretching using a separate forging machine after using a jig for necking. That is, a troublesome process can be reduced. Thus, although the number of times of reheating is reduced, a preform for a high-accuracy turbine blade can be manufactured.
  • the present invention even a difficult-to-work material used for a turbine blade can be easily necked using a radial forging machine.
  • the novel hot forging method using a radial forging machine the number of times of reheating a forging material can be significantly reduced, the productivity can be improved, and this method is extremely effective in power saving.
  • the hot forging die 1 according to the present invention shown in Fig. 2 was prepared.
  • a necking portion 5 of the prepared hot forging die 1 for necking includes a pair of halved pressing portions between which the forging material is interposed, in which each of the halved pressing portions has a convex portion having a substantially semicircular cross-section which is continuous so as to surround the forging material, and each of the halved pressing portions includes a rough processing portion and a finishing portion having a convex portion having a larger curvature radius than the rough processing portion.
  • the curvature radius of the necking portion 5 gradually changes, in which the curvature radius of the substantially semicircular convex portion of the rough processing portion 13 is 30 mm, and the curvature radius of the substantially semicircular convex portion of the finishing portion 14 is 50 mm.
  • the stretching portion 7 for stretching includes a pair of halved pressing portions 12 between which the forging material is interposed, in which each of the halved pressing portions 12 has a substantially semicircular convex shape which is continuous so as to surround the forging material, and each of the halved pressing portions 12 includes a substantially flat rough processing portion 13 and a finishing portion 14.
  • the width of the pressing portion for stretching gradually changes, in which the width of the rough processing portion 13 is 50 mm, and the width of the finishing portion 14 is 100 mm. Stretching was performed using a hot forging die having a shape in which a final shape was emphasized.
  • the above-described two hot forging dies were set as a pair, and the pair of hot forging dies were attached to a radial forging machine.
  • a forging material for a 50-inch turbine blade was heated in a heating furnace heated to 950°C.
  • the forging material was formed of a titanium alloy, in which the diameter was ⁇ 200 mm and the length was 1100 mm.
  • the forging material was extracted from the heating furnace and started to be hot-forged in the radial forging machine.
  • the forging material was held by a manipulator.
  • the forging material was necked by rotating the heated forging material 21 and concurrently pressing the forging material using each of the halved pressing portions of the pair of two hot forging dies 1 which were facing each other.
  • the forging material was hot-forged into a predetermined shape while rotating the forging material at the same position (not moving in the longitudinal direction of the forging material).
  • a plurality of halved pressing portions 2 for necking were formed in one die, and two portions were necked at the same time using this die.
  • the hot forging die was replaced with the hot forging die 11 including the pressing portion for stretching.
  • the forging material was extracted from the radial forging machine and was reheated to a predetermined forging temperature.
  • the forging material was attached to the radial forging machine again and was hot-forged using the pressing portion for stretching.
  • the forging material was intermittently rotated by the radial forging machine and was sequentially moved in the longitudinal direction such that the shape thereof was adjusted to a predetermined shape.
  • the forging material was hot-forged into a preform shape.
  • a preform 22 after hot forging had a shape shown in Fig. 7 which was suitable for forming a root portion, a wing portion, or a boss portion. In the preform after hot forging, a preform such as an overlap defect did not occur.
  • Example 2 the effect of the hot forging die shown in Fig. 8 was verified.
  • the same hot forging die for necking as in Example 1 was used.
  • the stretching portion 7 for stretching includes a pair of halved pressing portions 12 between which the forging material is interposed, in which each of the halved pressing portions 12 has a substantially semicircular convex shape which is continuous so as to surround the forging material, and each of the halved pressing portions 12 includes a substantially flat rough processing portion 13 and a finishing portion 14.
  • the width of the pressing portion for stretching gradually changes, in which the width of the rough processing portion 13 is 50 mm, and the width of the finishing portion 14 is 100 mm.
  • a concave portion having a width of 80 mm was formed at the center of the finishing portion, and the number of pressing portions in the finishing portion was 2.
  • the width of each of the two divided pressing portions was 270 mm.
  • the same hot forging die for necking as in Example 1 was used.
  • a forging material for a 50-inch turbine blade was heated in a heating furnace heated to 950°C.
  • the forging material was formed of a titanium alloy, in which the diameter was ⁇ 200 mm and the length was 1100 mm.
  • the forging material was extracted from the heating furnace and started to be hot-forged in the radial forging machine.
  • the forging material was held by a manipulator.
  • the forging material was necked by rotating the heated forging material 21 and concurrently pressing the forging material using each of the halved pressing portions of the pair of two hot forging dies 1 which were facing each other.
  • the forging material was hot-forged in a predetermined shape while rotating the forging material at the same position (not moving in the longitudinal direction of the forging material).
  • a plurality of halved pressing portions 12 for necking were formed in one die, and two portions were necked at the same time using this die.
  • the hot forging die was replaced with the hot forging die 11 of Fig. 3 including the pressing portion for stretching.
  • the forging material was extracted from the radial forging machine and was reheated to a predetermined forging temperature.
  • the forging material was attached to the radial forging machine again and was hot-forged using the pressing portion for stretching.
  • the forging material was intermittently rotated by the radial forging machine and was sequentially moved in the longitudinal direction such that the shape thereof was adjusted to a predetermined shape. As a result, the forging material was hot-forged into a preform shape.
  • the hot forging die was replaced with the hot forging die 11 shown in Fig.
  • a preform 22 after hot forging had a shape shown in Fig. 5 which was suitable for forming a root portion, a wing portion, or a boss portion. In the preform after hot forging, a preform such as an overlap defect did not occur. Regarding the bending of the preform having a total length of about 1500 mm, it was verified that bending of about 5 mm was suppressed by comparing the preform obtained in Example 2 to the preform obtained in Example 1.
  • a difficult-to-work material used for a turbine blade or the like can be easily stretched using a radial forging machine.
  • a forging material can be hot-forged and necked into a predetermined preform shape using a radial forging machine. Therefore, unlike the related art, a troublesome process such as use of a jig for necking can be reduced. Thus, although the number of times of reheating is reduced, a preform for a high-accuracy turbine blade can be manufactured.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Forging (AREA)
EP16776474.5A 2015-04-06 2016-03-31 Matrice de forgeage à chaud et procédé de forgeage à chaud Active EP3281719B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2015077337 2015-04-06
PCT/JP2016/060732 WO2016163307A1 (fr) 2015-04-06 2016-03-31 Matrice de forgeage à chaud et procédé de forgeage à chaud

Publications (3)

Publication Number Publication Date
EP3281719A1 true EP3281719A1 (fr) 2018-02-14
EP3281719A4 EP3281719A4 (fr) 2018-12-19
EP3281719B1 EP3281719B1 (fr) 2020-09-23

Family

ID=57072486

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16776474.5A Active EP3281719B1 (fr) 2015-04-06 2016-03-31 Matrice de forgeage à chaud et procédé de forgeage à chaud

Country Status (4)

Country Link
EP (1) EP3281719B1 (fr)
JP (1) JP6108258B2 (fr)
ES (1) ES2835953T3 (fr)
WO (1) WO2016163307A1 (fr)

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US611574A (en) * 1898-09-27 Die fob and method of swaging metallic balls
AT320383B (de) * 1973-05-17 1975-02-10 Gfm Fertigungstechnik Werkzeug für Durchlaufschmiedemaschinen
JPS5854900B2 (ja) * 1976-07-05 1983-12-07 株式会社神戸製鋼所 フランジ付軸材の成形方法及び成形装置
JPS561236A (en) * 1979-06-18 1981-01-08 Nippon Steel Corp Production of rough shape billet by forging
JPS55136535A (en) * 1979-04-10 1980-10-24 Sumitomo Metal Ind Ltd Roughening method in die forging
JPS60250843A (ja) * 1984-05-28 1985-12-11 Daido Steel Co Ltd 背切り加工用の刃
JP3208818B2 (ja) * 1992-02-28 2001-09-17 石川島播磨重工業株式会社 プレス用金型およびプレス方法
JPH07185725A (ja) * 1993-12-28 1995-07-25 Daido Steel Co Ltd ロールとその製造方法
RU2220020C1 (ru) * 2002-04-04 2003-12-27 Открытое акционерное общество "Чепецкий механический завод" Способ изготовления поковок преимущественно из металлов и сплавов подгруппы титана и ковочный комплекс для его осуществления
PL2149411T3 (pl) * 2008-07-29 2012-02-29 Magna Powertrain Ag & Co Kg Młotek do kucia na kowarce

Also Published As

Publication number Publication date
JP6108258B2 (ja) 2017-04-05
EP3281719B1 (fr) 2020-09-23
EP3281719A4 (fr) 2018-12-19
JPWO2016163307A1 (ja) 2017-04-27
WO2016163307A1 (fr) 2016-10-13
ES2835953T3 (es) 2021-06-23

Similar Documents

Publication Publication Date Title
JP2013513055A (ja) タービンエンジンブレード用の金属補強材の製造方法
US5694683A (en) Hot forming process
JP6774625B2 (ja) 熱間鍛造用金型及び熱間鍛造方法
KR20020072859A (ko) 언벤딩 형상의 예비성형체를 이용하는 크랭크스로우 단조공법 및 단조장치
EP2623229B1 (fr) Procédé de fabrication d'une pale
CN105458631B (zh) 轮圈的制作方法及轮圈制作用轧辊组
EP3281720B1 (fr) Matrice de forgeage à chaud et procédé de forgeage à chaud
EP3281719B1 (fr) Matrice de forgeage à chaud et procédé de forgeage à chaud
JP6541024B2 (ja) 熱間鍛造用金型及び熱間鍛造方法
CN106345966B (zh) 一种汽车下摆臂生产工艺
CN205324588U (zh) 一种斗齿的剖分式锻造模具
JP6206739B2 (ja) タービンブレードの製造方法
US2972181A (en) Process for making turbine blades
JP6761579B2 (ja) 熱間鍛造用金型及び熱間鍛造方法
US10543523B2 (en) Forging tool for the manufacturing of a shaped rolled ring, notably for the manufacture of a turbomachine disc
JP6738537B2 (ja) 熱間鍛造方法
JP6761576B2 (ja) 曲り取り用金型及び曲り取り方法並びにタービンブレード用荒地の製造方法
US2328348A (en) Manufacture of propeller blades
US20160256954A1 (en) Method and system for diffusion bonded components having internal passages
RU2387507C2 (ru) Способ изготовления крупногабаритных изделий переменного сечения из легких сплавов
EP3028787B1 (fr) Appareil et méthode de forgeage
CN110089816B (zh) 一种手镯制作方法
RU158818U1 (ru) Кольцевая заготовка для получения кольцевых деталей корпусов камер сгорания газотурбинных двигателей
RU2366530C1 (ru) Способ изготовления полой лопатки
RU2597852C2 (ru) Полукорпус шарового крана и способ его изготовления

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20171006

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
A4 Supplementary search report drawn up and despatched

Effective date: 20181120

RIC1 Information provided on ipc code assigned before grant

Ipc: B21J 13/02 20060101AFI20181114BHEP

Ipc: B21J 1/04 20060101ALI20181114BHEP

Ipc: B21K 3/04 20060101ALI20181114BHEP

Ipc: B21J 7/14 20060101ALI20181114BHEP

Ipc: B21J 5/00 20060101ALI20181114BHEP

Ipc: B21J 9/06 20060101ALI20181114BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: B21J 7/14 20060101ALI20200326BHEP

Ipc: B21J 5/00 20060101ALI20200326BHEP

Ipc: B21J 9/06 20060101ALI20200326BHEP

Ipc: B21J 13/02 20060101AFI20200326BHEP

Ipc: B21J 1/04 20060101ALI20200326BHEP

Ipc: B21K 3/04 20060101ALI20200326BHEP

INTG Intention to grant announced

Effective date: 20200414

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602016044581

Country of ref document: DE

Ref country code: AT

Ref legal event code: REF

Ref document number: 1315871

Country of ref document: AT

Kind code of ref document: T

Effective date: 20201015

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201223

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201224

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201223

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200923

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210125

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210123

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2835953

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20210623

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602016044581

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: AT

Ref legal event code: UEP

Ref document number: 1315871

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

26N No opposition filed

Effective date: 20210624

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20210331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210331

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210331

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210331

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210331

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230208

Year of fee payment: 8

Ref country code: AT

Payment date: 20230227

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20230213

Year of fee payment: 8

Ref country code: GB

Payment date: 20230209

Year of fee payment: 8

Ref country code: DE

Payment date: 20230131

Year of fee payment: 8

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200923

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20160331

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20230404

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: AT

Payment date: 20240226

Year of fee payment: 9

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240206

Year of fee payment: 9

Ref country code: GB

Payment date: 20240208

Year of fee payment: 9