CN109317588B - Forging method and die for blade of aero-engine - Google Patents
Forging method and die for blade of aero-engine Download PDFInfo
- Publication number
- CN109317588B CN109317588B CN201811200038.8A CN201811200038A CN109317588B CN 109317588 B CN109317588 B CN 109317588B CN 201811200038 A CN201811200038 A CN 201811200038A CN 109317588 B CN109317588 B CN 109317588B
- Authority
- CN
- China
- Prior art keywords
- extrusion
- blank
- die
- groove
- cavity
- 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.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/002—Hybrid process, e.g. forging following casting
-
- 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
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/02—Die forging; Trimming by making use of special dies ; Punching during forging
- B21J5/025—Closed die forging
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/06—Methods for forging, hammering, or pressing; Special equipment or accessories therefor for performing particular operations
- B21J5/08—Upsetting
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Forging (AREA)
Abstract
The invention provides a forging method and a die for an aircraft engine blade. The forging method of the blade of the aircraft engine comprises the following steps: a. blanking the blank; b. spraying a glass lubricant on the surface of the blank; c. heating the blank to a temperature above the recrystallization temperature and keeping the temperature; d. placing the blank into an extrusion cavity of a preheated die, and extruding to obtain an extrusion rod piece; e. after the extrusion of the rod is finished, the extrusion rod piece is placed into an upsetting cavity of the die within 4-6 s, and upsetting is carried out to obtain an upsetting piece; f. and after the heading is finished, putting the heading piece into a finish forging cavity of a die within 4-6 s, and performing finish forging to obtain the blade. Because the extrusion cavity, the heading cavity and the finish forging cavity are arranged on the same die, the time intervals between the extrusion rod and the heading and between the heading and the finish forging are very short, the temperature reduction of the extrusion rod piece and the heading piece is very limited, and the whole forging process only needs to heat the blank once.
Description
Technical Field
The invention relates to the technical field of forging of blades of aero-engines, in particular to a forging method and a forging die for blades of aero-engines.
Background
A blade is a key component in an aircraft engine. The process flow of the traditional mainstream blade forging method is as follows: blanking → extruding rod → heading → finish forging. Wherein, the extrusion of the rod, the heading and the final forging are single working procedures, three times of fire are needed, and three sets of dies and a plurality of devices are needed. The fire number is many, the frock quantity is many, the technological process is complicated, manufacturing cost is high.
Disclosure of Invention
The invention provides a forging method and a die for an aircraft engine blade, and aims to solve the problems of multiple fire times, multiple tools, complex process and high production cost of a mainstream blade forging method.
The technical scheme adopted by the invention is as follows:
the invention provides a forging method of an aircraft engine blade, which comprises the following steps: a. blanking the blank; b. spraying a glass lubricant on the surface of the blank; c. heating the blank to a temperature above the recrystallization temperature and keeping the temperature; d. placing the blank into an extrusion cavity of a preheated die, and extruding to obtain an extrusion rod piece; e. after the extrusion of the rod is finished, the extrusion rod piece is placed into an upsetting cavity of the die within 4-6 s, and upsetting is carried out to obtain an upsetting piece; f. and after the heading is finished, putting the heading piece into a finish forging cavity of a die within 4-6 s, and performing finish forging to obtain the blade.
Further, the blanking of the blank in the step a specifically comprises: and sawing the blank into a bar stock, and rounding off the two ends of the bar stock.
Further, the step b of spraying the glass lubricant on the surface of the blank specifically comprises: heating the blank at the temperature of 100-120 ℃ and preserving the heat for 30-60 min; spraying a glass lubricant on the surface of the blank, wherein the spraying thickness of the glass lubricant is 0.4-0.8 mm; heating the blank at the temperature of 100-120 ℃ and preserving the heat for 40-80 min.
Further, the blank is a TC4 titanium alloy blank, the heating temperature in the step c is the temperature of the transformation point of the TC4 titanium alloy β minus 50 ℃, and the heat preservation time is 1-2 times of the diameter of the TC4 titanium alloy blank.
Further, the mould in the step d is preheated to 180-230 ℃.
Further, the forging method of the blade of the aircraft engine further comprises the step of cutting off the flash of the blade.
The die comprises a female die and a male die which are arranged oppositely, wherein a first extrusion groove, a first upsetting groove and a first finish forging groove are formed in one side of the female die, a second extrusion groove, a second upsetting groove and a second finish forging groove are formed in the side, opposite to the female die, of the male die, the female die and the male die are stressed to be closed mutually, so that the first extrusion groove and the second extrusion groove are closed mutually to form an extrusion cavity for extruding a rod, the first upsetting groove and the second upsetting groove are closed mutually to form an upsetting cavity for upsetting, the first finish forging groove and the second finish forging groove are closed mutually to form a finish forging cavity for finish forging, and the die further comprises an extrusion punch for extruding the rod by matching with the extrusion cavity and an upsetting punch for upsetting by matching with the upsetting cavity.
Furthermore, a first extrusion insert is detachably mounted on the female die, a second extrusion insert is detachably mounted on the male die, the first extrusion groove is formed in the first extrusion insert, and the second extrusion groove is formed in the second extrusion insert, so that the first extrusion insert and/or the second extrusion insert can be conveniently replaced when being worn.
Furthermore, the first finish forging groove is formed in the middle of the female die, and the second finish forging groove is formed in the middle of the male die, so that a finish forging cavity formed by mutual closing of the first finish forging groove and the second finish forging groove is located in the middle of the die, and dislocation of the female die and the male die due to the action of eccentric force of the die during finish forging is avoided.
Furthermore, a first positioning groove is formed in the notch of the first finish forging groove, a second positioning groove is formed in the notch of the second finish forging groove, and the first positioning groove and the second positioning groove are mutually closed to form a finish forging positioning groove for positioning the rod part of the heading piece to avoid the heading piece rolling in the finish forging cavity.
The invention has the following beneficial effects:
according to the forging method of the blade of the aero-engine, the blank is heated to the temperature above the recrystallization temperature and is kept warm, so that the blank is subjected to thermal deformation and is convenient for rod extrusion. Obtaining an extrusion rod piece after the billet finishes extruding the rod in the extrusion cavity, and placing the extrusion rod piece into an upsetting cavity for upsetting; and upsetting the extruded rod piece in the upsetting die cavity to obtain an upsetting piece, and then placing the upsetting piece into a finish forging die cavity for finish forging. Because the extrusion cavity, the upset head cavity and the finish forging cavity are arranged on the same die, the time intervals between the extrusion rod and the upset head and between the upset head and the finish forging are very short, and the temperature reduction of the extrusion rod piece and the upset head piece is very limited. In addition, the billet may have a certain temperature rise due to the heat of deformation during the extrusion of the rod. The temperatures of the rod extrusion piece and the heading piece can still reach the recrystallization temperature, so that the heading and the finish forging can be continuously carried out after the rod extrusion, and the whole forging process only needs to heat the blank once. Before the blank is heated, the surface of the blank is firstly sprayed with the glass lubricant, and the glass lubricant can form a compact and firm film layer in the heating process, so that the lubricating effect can be achieved, air can be isolated, the blank can be prevented from being oxidized, and the temperature drop in the blank transfer process can be reduced. The blade forging method for the aero-engine blade provided by the invention is adopted to forge the blade, only one device and one set of die are needed, the blade can be forged within one fire, and the blade forging method has the advantages of low production cost and simple process route.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic flow diagram of a method of forging an aircraft engine blade in accordance with a preferred embodiment of the invention;
FIG. 2 is one of the schematic illustrations of a die for aircraft engine blade forging of the preferred embodiment of the present invention;
FIG. 3 is a second schematic view of a die for forging an aircraft engine blade according to a preferred embodiment of the invention.
Description of reference numerals:
1. a female die; 2. a male mold; 3. extruding the cavity; 4. a heading cavity; 5. finish forging the die cavity; 6. extruding the punch; 7. heading punch; 8. a first extrusion insert; 9. and finally forging the positioning groove.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic flow diagram of a method of forging an aircraft engine blade in accordance with a preferred embodiment of the invention; FIG. 2 is one of the schematic illustrations of a die for aircraft engine blade forging of the preferred embodiment of the present invention; FIG. 3 is a second schematic view of a die for forging an aircraft engine blade according to a preferred embodiment of the invention.
As shown in fig. 1, the forging method of the blade of the aircraft engine of the embodiment includes the following steps: a. blanking the blank; b. spraying a glass lubricant on the surface of the blank; c. heating the blank to a temperature above the recrystallization temperature and keeping the temperature; d. placing the blank into an extrusion cavity 3 of a preheated die, and extruding to obtain an extrusion rod piece; e. after the rod extrusion is finished, the rod extrusion part is placed into an upsetting cavity 4 of the die within 4-6 s, and upsetting is carried out to obtain an upsetting part; f. and after the heading is finished, putting the heading piece into a finish forging cavity 5 of the die within 4-6 s, and performing finish forging to obtain the blade. According to the forging method of the blade of the aero-engine, the blank is heated to the temperature above the recrystallization temperature and is kept warm, so that the blank is subjected to thermal deformation and is convenient for rod extrusion. Obtaining an extrusion rod piece after the billet finishes extruding the rod in the extrusion cavity 3, and placing the extrusion rod piece into the heading cavity 4 for heading; and upsetting the extrusion rod piece in the upsetting cavity 4 to obtain an upsetting piece, and then placing the upsetting piece into a finish forging cavity 5 for finish forging. Because the extrusion cavity 3, the upset head cavity 4 and the finish forging cavity 5 are arranged on the same die, the time intervals between the extrusion rod and the upset head and between the upset head and the finish forging are very short, and the temperature reduction of the extrusion rod piece and the upset head piece is very limited. In addition, the billet may have a certain temperature rise due to the heat of deformation during the extrusion of the rod. The temperatures of the rod extrusion piece and the heading piece can still reach the recrystallization temperature, so that the heading and the finish forging can be continuously carried out after the rod extrusion, and the whole forging process only needs to heat the blank once. Before the blank is heated, the surface of the blank is firstly sprayed with the glass lubricant, and the glass lubricant can form a compact and firm film layer in the heating process, so that the lubricating effect can be achieved, air can be isolated, the blank can be prevented from being oxidized, and the temperature drop in the blank transfer process can be reduced. The blade forging method for the aero-engine blade provided by the invention is adopted to forge the blade, only one device and one set of die are needed, the blade can be forged within one fire, and the blade forging method has the advantages of low production cost and simple process route.
In this embodiment, the blanking of the blank in the step a specifically includes: and sawing the blank into a bar stock, and rounding off the two ends of the bar stock. The bar stock is slender and is suitable for extruding the rod. The filleting angles at the two ends of the bar stock can prevent burrs from existing in notches of the blank after blanking is completed, and the burrs are extruded into the extrusion rod piece to form folding when the extrusion rod is extruded.
In this embodiment, the step b of spraying the glass lubricant on the surface of the blank specifically includes: heating the blank at the temperature of 100-120 ℃ and preserving the heat for 30-60 min; spraying a glass lubricant on the surface of the blank, wherein the spraying thickness of the glass lubricant is 0.4-0.8 mm; heating the blank at the temperature of 100-120 ℃ and preserving the heat for 40-80 min. If the glass lubricant is sprayed directly on the surface of the blank and is in a liquid state, the glass lubricant will flow downwards under the action of gravity, so that the upper part of the blank has no glass lubricant, and the lower part of the blank has thick glass lubricant. Before spraying the glass lubricant, the blank is heated and insulated, then the glass lubricant is sprayed on the surface of the blank, water in the glass lubricant is heated and evaporated, the glass lubricant does not flow, the glass lubricant can be attached to the surface of the blank, and an even lubricating layer can be formed on the surface of the blank to play a role in lubrication. Too thick a spray thickness of the glass lubricant results in a build up of glass lubricant which affects the size of the blade when forging is performed. The spraying thickness of the glass lubricant is too thin, so that the lubricating layer is pressed and broken during forging, the lubricating effect is not achieved, and the surface quality of the blade is poor. After the glass lubricant is sprayed, the blank is heated and insulated, so that the glass lubricant can be further dried, and the adhesive force of the glass lubricant is further improved.
In the embodiment, the blank is a TC4 titanium alloy blank, the heating temperature in the step c is the temperature of the transformation point of TC4 titanium alloy β minus 50 ℃, the holding time is 1-2 times of the diameter of the TC4 titanium alloy blank, the heating temperature of the blank is related to the type of the blank, for the TC4 titanium alloy blank, the heating temperature is the temperature of the transformation point of TC4 titanium alloy β minus 50 ℃, under the temperature, the TC4 titanium alloy blank cannot generate β phase transformation and can reach the recrystallization temperature, and the blank is conveniently extruded, the holding time is 1-2 times of the diameter of the TC4 titanium alloy blank, and the holding time is understood to be min as the unit, the diameter is mm as the unit, the holding time is 1-2 times of the diameter too long value, for example, the diameter is 30mm, and the holding time is enough for the inside of the blank to reach the recrystallization temperature, and the holding time can increase the cost.
In this embodiment, the mold in step d is preheated to 180-230 ℃. The mould is preheated to 180-230 ℃ to prevent the temperature difference between the mould and the blank from being overlarge, and the temperature of the surface of the mould is prevented from being higher than the temperature inside the mould and the temperature of the surface of the blank is prevented from being lower than the temperature inside the blank, so that the mould and the blank are prevented from deforming.
In this embodiment, the forging method for the blade of the aircraft engine further includes the step of cutting off the flash of the blade. After the blade is forged, flash is easy to remain, and the quality of the blade is affected. The flash can be cut off by adopting a trimming die or a laser cutting machine, so that the quality of the blade is ensured.
As shown in fig. 2 and 3, a preferred embodiment of the present invention further provides a die for forging an aircraft engine blade, which includes a female die 1 and a male die 2 that are oppositely arranged, wherein a first extrusion groove, a first upset groove and a first finish forging groove are formed on one side of the female die 1, a second extrusion groove, a second upset groove and a second finish forging groove are formed on one side of the male die 2 opposite to the female die 1, the female die 1 and the male die 2 are forced to be closed with each other, so that the first extrusion groove and the second extrusion groove are mutually closed to form an extrusion cavity 3 for extruding a rod, the first upsetting groove and the second upsetting groove are mutually closed to form an upsetting cavity 4 for upsetting, and the first finish forging groove and the second finish forging groove are mutually closed to form a finish forging cavity 5 for finish forging, the die further comprises an extrusion punch 6 for being matched with the extrusion cavity 3 to extrude the rod and an upsetting punch 7 for being matched with the upsetting cavity 4 to upset. The female die 1 and the male die 2 are mutually closed under the action of equipment to form an extrusion cavity 3, an upset head cavity 4 and a finish forging cavity 5. When extruding the rod, the blank is put into the extrusion cavity 3, and the blank is extruded into the slender forming cavity of the extrusion cavity 3 under the action of the extrusion punch 6, so as to obtain the rod extruding rod with a head part and a slender rod part. When heading, the rod part of the extrusion rod piece is placed into the positioning cavity of the heading cavity 4, and the head part of the extrusion rod piece forms a tenon under the action of the heading punch 7, so that the heading piece is obtained. And when final forging is carried out, putting the tenon of the upset head piece into the tenon cavity of the final forging cavity 5, mutually closing the female die 1 and the male die 2 under the action of equipment, and pressing the rod part of the upset head piece to form a blade body and a flange plate to obtain the blade.
In the present embodiment, as shown in fig. 2 and 3, a first insert 8 is detachably mounted on the female die 1, a second insert is detachably mounted on the male die 2, a first extrusion groove is formed on the first insert 8, and a second extrusion groove is formed on the second insert, so that the first insert 8 and/or the second insert can be easily replaced when worn. The extrusion die cavity 3 is a part for forming the extrusion rod piece, the extrusion die cavity 3 is designed into an insert structure due to fast extrusion deformation and abrasion, when the first extrusion insert 8 and/or the second extrusion insert are abraded to the extent that the size of the extrusion rod piece cannot be ensured, the first extrusion insert 8 and/or the second extrusion insert can be directly taken out for replacement, and the maintenance cost of the die is low.
As shown in fig. 2 and 3, in the present embodiment, the first finish forging groove is opened in the middle of the female die 1, and the second finish forging groove is opened in the middle of the male die 2, so that the finish forging cavity 5 formed by closing the first finish forging groove and the second finish forging groove is in the middle of the die, thereby avoiding the misalignment between the female die 1 and the male die 2 caused by the eccentric force applied to the die during finish forging. The final forging cavity 5 is positioned in the middle of the die, so that when the upset head piece is subjected to final forging, the stress center of the upset head piece is superposed with the force application center of the equipment, the dislocation of the female die 1 and the male die 2 caused by the eccentric force of the die is avoided, and the size accuracy of the blade is improved. Optionally, the extrusion cavity 3 is on one side of the die and the heading cavity 4 is on the other side of the die away from the extrusion cavity 3.
In the present embodiment, as shown in fig. 2 and 3, a first positioning groove is provided at the notch of the first finish forging groove, a second positioning groove is provided at the notch of the second finish forging groove, and the first positioning groove and the second positioning groove are closed to each other to form a finish forging positioning groove 9 for positioning the stem of the heading member at the time of finish forging so as to avoid rolling of the heading member in the finish forging cavity 5. When finish forging is carried out, the rod part of the upset head piece is placed in the finish forging positioning groove 9, the upset head piece can be prevented from rolling in the finish forging cavity 5, accurate positioning of the upset head piece in the finish forging cavity 5 is achieved, and the defect that the blade is not full is avoided.
In specific implementation, a forging method of an aircraft engine blade is provided. The specific process of blade forging on a horizontal split die horizontal forging machine is described in detail below by taking the TC4 titanium alloy blade forging method as an example.
1) The TC4 titanium alloy blank is sawn into a phi 30 × 45 bar stock, and the two ends of the bar stock are rounded R3.
2) And (3) putting the blanked TC4 titanium alloy blank into an electric furnace with the heating temperature of 120 ℃ for heating and preserving the heat for 40 min.
3) And after the specified heat preservation time is reached, taking the TC4 titanium alloy blank out of the electric furnace, spraying a titanium alloy extruded glass lubricant on the surface, and spraying the titanium alloy extruded glass lubricant to the thickness of 0.5 mm.
4) And (3) putting the blank sprayed with the glass lubricant into an electric furnace at 120 ℃ for heating and preserving heat for 60 min.
5) And taking the blank out of the electric furnace, transferring the blank into the electric furnace with the heating temperature of 960 ℃, heating and preserving heat for 30 min.
6) And after the specified heat preservation time is reached, taking the blank out of the electric furnace, putting the blank into an extrusion cavity 3 of a die, stepping down a pedal plate for controlling the horizontal split die horizontal forging machine to operate by an operator, closing the die, and ejecting an extrusion punch 6 forwards to obtain an extrusion rod piece.
7) And after the extrusion rod is extruded, the die is automatically opened, the extrusion rod piece is taken out of the extrusion cavity 3 of the die and is placed into the heading cavity 4 of the die within 5s, an operator steps on a pedal, the die is closed, and the heading punch 7 is ejected forwards to obtain the heading piece.
8) And after the heading is finished, automatically opening the die, taking the heading piece out of the heading cavity 4 of the die within 5s, putting the heading piece into a finish forging cavity 5 of the die, stepping down a pedal by an operator, and closing the die to obtain the blade.
9) The flash of the blade was cut off using a laser cutter.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A forging method of an aircraft engine blade is characterized by comprising the following steps:
a. blanking the blank;
b. heating the blank at the temperature of 100-120 ℃ and keeping the temperature for 30-60 min, spraying a glass lubricant on the surface of the blank to evaporate water in the glass lubricant under heating, so that the glass lubricant does not flow, and the glass lubricant is attached to the surface of the blank to form a uniform lubricating layer;
c. heating the blank to a temperature above the recrystallization temperature and keeping the temperature;
d. placing the blank into an extrusion cavity (3) of a preheated die, and extruding to obtain an extrusion rod piece;
e. after the extrusion of the rod is finished, the extrusion rod piece is placed into an upsetting cavity (4) of the die within 4-6 s, and upsetting is carried out to obtain an upsetting piece;
f. after heading is finished, the heading piece is placed into a finish forging cavity (5) of the die within 4 s-6 s for finish forging to obtain a blade;
the die comprises a female die (1) and a male die (2) which are oppositely arranged, a first extrusion groove, a first heading groove and a first finish forging groove are formed in one side of the female die (1), a second extrusion groove, a second heading groove and a second finish forging groove are formed in one side of the male die (2) opposite to the female die (1),
the female die (1) and the male die (2) are stressed to be mutually closed, so that the first extrusion groove and the second extrusion groove are mutually closed to form an extrusion cavity (3) for extruding a rod, the first upsetting groove and the second upsetting groove are mutually closed to form an upsetting cavity (4) for upsetting, and the first finish forging groove and the second finish forging groove are mutually closed to form a finish forging cavity (5) for finish forging,
the die further comprises an extrusion punch (6) which is used for being matched with the extrusion cavity (3) to extrude the rod and an upset punch (7) which is used for being matched with the upset cavity (4) to upset.
2. The aircraft engine blade forging method according to claim 1,
the blanking of the blank in the step a is as follows: and sawing the blank into a bar stock, and rounding off the two ends of the bar stock.
3. The aircraft engine blade forging method according to claim 1,
the step b of spraying the glass lubricant on the surface of the blank specifically comprises the following steps: spraying a glass lubricant on the surface of the blank, wherein the spraying thickness of the glass lubricant is 0.4-0.8 mm; heating the blank at the temperature of 100-120 ℃ and preserving the heat for 40-80 min.
4. The aircraft engine blade forging method according to claim 1,
the blank is a TC4 titanium alloy blank, the heating temperature in the step c is the temperature of the transformation point of the TC4 titanium alloy β minus 50 ℃, and the heat preservation time is 1-2 times of the diameter of the TC4 titanium alloy blank.
5. The aircraft engine blade forging method according to claim 1,
and d, preheating the die in the step d to 180-230 ℃.
6. The aircraft engine blade forging method according to claim 1,
the forging method of the blade of the aircraft engine further comprises the step of cutting off the flash of the blade.
7. The aircraft engine blade forging method according to claim 1,
the female die is characterized in that a first extrusion insert (8) is detachably mounted on the female die (1), a second extrusion insert is detachably mounted on the male die (2), a first extrusion groove is formed in the first extrusion insert (8), and a second extrusion groove is formed in the second extrusion insert.
8. The aircraft engine blade forging method according to claim 1,
the first finish forging groove is formed in the middle of the female die (1), the second finish forging groove is formed in the middle of the male die (2), and therefore a finish forging cavity (5) formed by the mutual closing of the first finish forging groove and the second finish forging groove is located in the middle of the die.
9. The aircraft engine blade forging method according to claim 1,
the notch department in first finish forging groove is equipped with first constant head tank, the notch department in second finish forging groove is equipped with the second constant head tank, first constant head tank with the second constant head tank is closed each other and is formed the pole portion to the heading piece when being used for carrying on finish forging and fixes a position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811200038.8A CN109317588B (en) | 2018-10-16 | 2018-10-16 | Forging method and die for blade of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811200038.8A CN109317588B (en) | 2018-10-16 | 2018-10-16 | Forging method and die for blade of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109317588A CN109317588A (en) | 2019-02-12 |
| CN109317588B true CN109317588B (en) | 2020-07-24 |
Family
ID=65262634
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811200038.8A Active CN109317588B (en) | 2018-10-16 | 2018-10-16 | Forging method and die for blade of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109317588B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110756714B (en) * | 2019-11-10 | 2021-08-06 | 中国航发南方工业有限公司 | High-speed extrusion forming die for blades |
| CN111496159A (en) * | 2019-12-06 | 2020-08-07 | 陕西宏远航空锻造有限责任公司 | Blank making method of GH2696 alloy small double-crown stator blade |
| CN112275971B (en) * | 2020-08-31 | 2022-08-26 | 中国航发南方工业有限公司 | Material gathering tool and forging method for titanium alloy eccentric variable-section blade |
| CN112743021B (en) * | 2020-12-24 | 2023-01-13 | 陕西宏远航空锻造有限责任公司 | Blank making method for forging compressor rotor blade |
| CN116441430B (en) * | 2023-06-19 | 2023-11-10 | 中国航发成都发动机有限公司 | Blade hot extrusion forming device |
| CN116571674B (en) * | 2023-06-20 | 2024-06-07 | 陕西长羽航空装备股份有限公司 | Machining equipment and machining method for aviation aircraft blade |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1246108C (en) * | 2002-10-23 | 2006-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for extruding and precisive roller forging thermal strength titanium alloy blades |
| CN106507725B (en) * | 2010-12-27 | 2014-04-23 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of method of high-temperature alloy blades precision form |
| DE102011105244A1 (en) * | 2011-02-04 | 2012-08-09 | Sms Meer Gmbh | Use of a heat upsetting method, use of a forming tool, method of producing a forging preform and forming apparatus or heat upsetting apparatus |
| CN102310154A (en) * | 2011-09-20 | 2012-01-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Die in alloy blade precision forging process |
| CN105583351B (en) * | 2015-12-19 | 2018-06-15 | 许昌中兴锻造有限公司 | The medium-sized flat forging process of slip shaft yoke |
| CN108188314B (en) * | 2018-03-09 | 2019-05-21 | 重庆禀天科技有限公司 | Band ear cylinder proper forgings One-time forging Whole fiber moulding process |
-
2018
- 2018-10-16 CN CN201811200038.8A patent/CN109317588B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN109317588A (en) | 2019-02-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109317588B (en) | Forging method and die for blade of aero-engine | |
| CN108500189A (en) | A kind of molding die with straight-edge conical cylinder forging and forging process for fuel method | |
| CN104108012B (en) | The forging method of one seed disk shaft integral part and the mould of use thereof | |
| CN104874713B (en) | A kind of continuous composite molding technique of oil injector body | |
| CN109622868B (en) | Forging method of T-shaped high-temperature alloy bolt forge piece | |
| CN111203504B (en) | Forging production method of large-size track shoe | |
| CN109676069A (en) | A kind of nozzle body precision forging method | |
| CN103381467A (en) | Opening and closing mold forming method for step type forge pieces | |
| CN105057529A (en) | Extrusion forming method for hollow shaft forged piece with variable cross section | |
| CN107671132B (en) | A kind of forming technology of speed torque-converters hub | |
| US2024285A (en) | Method of making pistons | |
| CN111014554A (en) | Forging process and forging die for deep hole shaft head | |
| CN102615126A (en) | Forming method for motorcycle starting shaft | |
| CN102319851B (en) | Cold precision forging technique for Z type contacts | |
| CN109351899B (en) | Forming method of large-scale multi-rib basin-shaped forging | |
| CN102500633A (en) | Method for forming cup-shaped component with gear | |
| US2743509A (en) | Method of making compressor blades | |
| US20170072455A1 (en) | Burr-freebolt forging mould | |
| CN109465369B (en) | Ring rolling forming device for rolling and bending single integral ring of special-shaped joint | |
| CN110883293A (en) | Knuckle one-die multi-cavity die and die forging process | |
| US2312095A (en) | Method of making hollow propellers | |
| CN109127974A (en) | A kind of forging method of helmet magnesium lithium-base alloy guide rail | |
| US2994952A (en) | Forging process | |
| CN106111879A (en) | A kind of moulding process of fuel injector nozzle | |
| US2593139A (en) | Plowshare manufacture |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |