CN109317588A - Blade of aviation engine forging method and mold - Google Patents
Blade of aviation engine forging method and mold Download PDFInfo
- Publication number
- CN109317588A CN109317588A CN201811200038.8A CN201811200038A CN109317588A CN 109317588 A CN109317588 A CN 109317588A CN 201811200038 A CN201811200038 A CN 201811200038A CN 109317588 A CN109317588 A CN 109317588A
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- Prior art keywords
- forging
- heading
- finish
- slot
- blade
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Classifications
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- 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
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- 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
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- 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
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- 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
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- 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
Abstract
The present invention provides a kind of blade of aviation engine forging method and molds.Blade of aviation engine forging method is the following steps are included: a, blanking blanks；B, in the surface sprayed glass lubricant of embryo material；C, embryo material is heated to recrystallization temperature or more and kept the temperature；D, embryo material is put into the extrusion pressing type chamber of preheated mold, carries out squeezing bar, obtain squeezing rod piece；E, it squeezes after the completion of bar, crowded rod piece is put into the heading type chamber of mold in 4s~6s, carry out heading, obtain heading part；F, after the completion of heading, heading part is put into the finish-forging type chamber of mold in 4s~6s, finish-forging is carried out, obtains blade.Since extrusion pressing type chamber, heading type chamber and finish-forging type chamber are arranged on the same mold, so that the time interval squeezed between bar and heading and heading and finish-forging is very short, the temperature decline for squeezing rod piece and heading part is extremely limited, so that entire forging process only needs to carry out primary heating to embryo material.
Description
Technical field
The present invention relates to blade of aviation engine technical field of forging, particularly, are related to a kind of blade of aviation engine forging
Make method and mold.
Background technique
Blade is one of aero-engine critical component.The process flow of the blade forging method of mainstream at present are as follows:
Blanking → squeeze bar → heading → finish-forging.Wherein squeezing bar, heading, finish-forging is single process, and three fire time need to be divided to carry out, need three sets
Mold and multiple devices.Fire time is more, tooling quantity is more, complex technical process, high production cost.
Summary of the invention
The present invention provides a kind of blade of aviation engine forging method and molds, to solve the blade forging method of mainstream
The problem of fiery secondary more, tooling quantity is more, complex technical process, high production cost.
The technical solution adopted by the invention is as follows:
One aspect of the present invention provides a kind of blade of aviation engine forging method, comprising the following steps: a, blanking blanks；
B, in the surface sprayed glass lubricant of embryo material；C, embryo material is heated to recrystallization temperature or more and kept the temperature；D, embryo material is put into
It in the extrusion pressing type chamber of preheated mold, carries out squeezing bar, obtains squeezing rod piece；E, it squeezes after the completion of bar, by crowded rod piece in 4s~6s
It is put into the heading type chamber of mold, carries out heading, obtain heading part；F, after the completion of heading, heading part is put into 4s~6s
In the finish-forging type chamber of mold, finish-forging is carried out, blade is obtained.
Further, the blanking blanks in step a specifically: embryo material is sawed into bar, in the both ends rounded corner of bar.
Further, the surface sprayed glass lubricant in embryo material in step b specifically: in 100 DEG C~120 DEG C of temperature
The lower heating embryo material of degree simultaneously keeps the temperature 30min~60min；It is thick in the spraying of the surface sprayed glass lubricant of embryo material, glass lubricant
Degree is 0.4mm~0.8mm；Embryo material and 40min~80min is kept the temperature in 100 DEG C~120 DEG C of at a temperature of heating.
Further, embryo material uses TC4 titanium alloy embryo material, and the heating temperature in step c is TC4 titanium alloy beta transformation temperature temperature
Degree subtracts 50 DEG C, and soaking time is 1 times~2 times of the diameter of TC4 titanium alloy embryo material.
Further, the mold in step d is preheated to 180 DEG C~230 DEG C.
Further, blade of aviation engine forging method further includes the steps that the cutting burrs of blade.
Another aspect of the present invention provides a kind of mold for blade of aviation engine forging, including the yin being oppositely arranged
Mould and formpiston, it is opposite with former that the side of former offers the first extruding slot, the first heading slot and the first finish-forging slot, formpiston
Side offers the second extruding slot, the second heading slot and the second finish-forging slot, former and is mutually closed with formpiston stress, so that first
It squeezes slot and is mutually closed extrusion pressing type chamber, the first heading slot and the second heading slot phase to be formed for squeeze bar with the second extruding slot
Mutually closure form heading type chamber for carrying out heading and the first finish-forging slot and the second finish-forging slot be mutually closed to be formed for into
The finish-forging type chamber of row finish-forging, mold further include for carrying out squeezing the extruding formed punch of bar and be used for and heading with the cooperation of extrusion pressing type chamber
The cooperation of type chamber carries out the heading formed punch of heading.
Further, the first extruding insert is detachably installed on former, the second extruding edge is detachably installed on formpiston
Block, the first extruding slot are opened in the first extruding insert, and the second extruding slot is opened in the second extruding insert, when the first extruding
It is convenient for replacing when insert and/or the second extruding insert abrasion.
Further, the first finish-forging slot is opened in the middle part of former, and the second finish-forging slot is opened in the middle part of formpiston, so that the
One finish-forging slot and the second finish-forging slot are mutually closed the middle part that the finish-forging type chamber to be formed is in mold, avoid carry out finish-forging when mold by
Eccentric force effect causes former to misplace with formpiston.
Further, it is equipped with the first locating slot at the notch of the first finish-forging slot, is equipped with second at the notch of the second finish-forging slot
Locating slot, the first locating slot and the second locating slot position the bar portion of heading part when being mutually closed to be formed for carrying out finish-forging
The finish-forging locating slot rolled in finish-forging type chamber to avoid heading part.
The invention has the following advantages:
Blade of aviation engine forging method of the invention, is heated to recrystallization temperature or more for embryo material and keeps the temperature, so that
Embryo material occurs thermal deformation and is convenient for squeezing bar.Bar is squeezed in extrusion pressing type chamber from embryo material to complete to obtain crowded rod piece, is put into crowded rod piece
Heading is carried out in heading type chamber；From crowded rod piece, heading is completed to obtain heading part in heading type chamber, then is put into finish-forging to heading part
Finish-forging is carried out in type chamber.Due to extrusion pressing type chamber, heading type chamber and finish-forging type chamber be arranged on the same mold so that squeeze bar and
Time interval between heading and heading and finish-forging is very short, and the temperature decline for squeezing rod piece and heading part is extremely limited.This
Outside, when squeezing bar, due to deformation heat, blank has certain temperature and rises blank.The temperature for squeezing rod piece and heading part still can
Enough reach recrystallization temperature, guarantee can be carried out continuously heading and finish-forging after squeezing bar, so that entire forging process only needs
Primary heating is carried out to embryo material.Before embryo material heating, first in the surface sprayed glass lubricant of embryo material, glass lubricant is adding
Fine and close and firm film layer can be formed in thermal process, can be played the role of lubrication, can also be completely cut off air, prevent embryo material oxygen
Change and reduce the temperature decline in embryo material transfer process.Blade is carried out using blade of aviation engine forging method of the invention
Forging, it is only necessary to equipment, an one set of die can complete the forging of blade in a fire time, have that production cost is low, work
The simple advantage of skill route.
Other than objects, features and advantages described above, there are also other objects, features and advantages by the present invention.
Below with reference to accompanying drawings, the present invention is described in further detail.
Detailed description of the invention
The attached drawing constituted part of this application is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is the flow diagram of the blade of aviation engine forging method of the preferred embodiment of the present invention；
Fig. 2 is one of the schematic diagram of mold for blade of aviation engine forging of the preferred embodiment of the present invention；
Fig. 3 is the two of the schematic diagram of the mold for blade of aviation engine forging of the preferred embodiment of the present invention.
Description of symbols:
1, former；2, formpiston；3, extrusion pressing type chamber；4, heading type chamber；5, finish-forging type chamber；6, formed punch is squeezed；7, heading formed punch；
8, first insert is squeezed；9, finish-forging locating slot.
Specific embodiment
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is the flow diagram of the blade of aviation engine forging method of the preferred embodiment of the present invention；Fig. 2 is the present invention
One of the schematic diagram of mold for blade of aviation engine forging of preferred embodiment；Fig. 3 is the preferred embodiment of the present invention
The two of the schematic diagram of mold for blade of aviation engine forging.
As shown in Figure 1, the blade of aviation engine forging method of the present embodiment, comprising the following steps: a, blanking blanks；b,
In the surface sprayed glass lubricant of embryo material；C, embryo material is heated to recrystallization temperature or more and kept the temperature；D, embryo material is put into pre-
It in the extrusion pressing type chamber 3 of the good mold of heat, carries out squeezing bar, obtains squeezing rod piece；E, it squeezes after the completion of bar, puts crowded rod piece in 4s~6s
Enter in the heading type chamber 4 of mold, carries out heading, obtain heading part；F, after the completion of heading, heading part is put into mould in 4s~6s
In the finish-forging type chamber 5 of tool, finish-forging is carried out, blade is obtained.Blade of aviation engine forging method of the invention, embryo material is heated to
It more than recrystallization temperature and keeps the temperature, so that embryo material occurs thermal deformation and is convenient for squeezing bar.It is complete that bar is squeezed in extrusion pressing type chamber 3 from embryo material
At crowded rod piece is obtained, it is put into heading type chamber 4 to crowded rod piece and carries out heading；From crowded rod piece, heading is completed in heading type chamber 4
To heading part, then it is put into finish-forging type chamber 5 to heading part and carries out finish-forging.Due to extrusion pressing type chamber 3, heading type chamber 4 and finish-forging type
Chamber 5 is arranged on the same mold, so that the time interval squeezed between bar and heading and heading and finish-forging is very short, squeezes rod piece
And the temperature decline of heading part is extremely limited.In addition, due to deformation heat, blank has in certain temperature blank when squeezing bar
It rises.The temperature for squeezing rod piece and heading part still is able to reach recrystallization temperature, and guarantee can be carried out continuously upsetting after squeezing bar
Head and finish-forging, so that entire forging process only needs to carry out primary heating to embryo material.Before embryo material heating, first in the table of embryo material
Face sprayed glass lubricant, glass lubricant can form fine and close and firm film layer during heating, can play lubrication
Effect, can also completely cut off air, prevent embryo material aoxidize and reduce embryo material transfer process in temperature decline.Using the present invention
Blade of aviation engine forging method carry out the forging of blade, it is only necessary to equipment, an one set of die, in a fire time
The forging for completing blade, has the advantages that production cost is low, process route is simple.
Blanking blanks in the present embodiment, in step a specifically: embryo material is sawed into bar, in the both ends rounding of bar
Angle.Bar is elongated, is appropriate for squeezing bar.There are hairs for the notch of embryo material after the completion of the both ends rounded corner of bar can prevent blanking
Thorn, burr is squeezed into crowded rod piece and forms folding when causing to carry out squeezing bar.
The surface sprayed glass lubricant in embryo material in the present embodiment, in step b specifically: at 100 DEG C~120 DEG C
At a temperature of heat and embryo material and keep the temperature 30min~60min；In the surface sprayed glass lubricant of embryo material, the spraying of glass lubricant
With a thickness of 0.4mm~0.8mm；Embryo material and 40min~80min is kept the temperature in 100 DEG C~120 DEG C of at a temperature of heating.If directly
In the surface sprayed glass lubricant of embryo material, glass lubricant is in a liquid state, and glass lubricant can be under gravity to dirty
It is dynamic, cause the top of embryo material there is no glass lubricant, and the glass lubricant of embryo material lower part is very thick.Sprayed glass lubricant it
Before, first embryo material is heated and is kept the temperature, then glass lubricant is sprayed on to the surface of embryo material, the moisture in glass lubricant by
Thermal evaporation, glass lubricant will not flow, and glass lubricant can be allowed to be attached to the surface of embryo material, can be formed on the surface of embryo material
One layer of uniform lubricant layer, to play the role of lubrication.The coating thickness of glass lubricant is blocked up to cause glass lubricant to be accumulated,
It will affect the vane size when being forged.The coating thickness of glass lubricant is excessively thin, and when being forged, lubricant layer is pressurized
Rupture, does not have the effect of lubrication, causes blade surface of poor quality.In sprayed glass lubricant and then embryo material is added
Heat is simultaneously kept the temperature, and glass lubricant can be made to be further dried, to further increase the adhesive force of glass lubricant.
In the present embodiment, embryo material uses TC4 titanium alloy embryo material, and the heating temperature in step c is TC4 titanium alloy beta transformation temperature
Temperature subtracts 50 DEG C, and soaking time is 1 times~2 times of the diameter of TC4 titanium alloy embryo material.The heating temperature of embryo material and the kind of embryo material
Class is related.For TC4 titanium alloy embryo material, heating temperature is that TC4 titanium alloy beta phase point temperature subtracts 50 DEG C.At this temperature,
TC4 titanium alloy embryo material will not occur β phase transformation and can reach recrystallization temperature, convenient for carrying out squeezing bar later to embryo material.Soaking time
It is 1 times~2 times of the diameter of TC4 titanium alloy embryo material, it is thus understood that soaking time as unit of min, protected as unit of mm by diameter
The numerical value of warm time is 1 times~2 times of the numerical value of diameter.For example, diameter is 30mm, soaking time can be 30min.This heat preservation
The inside of time enough embryo materials reaches recrystallization temperature, and soaking time is too long will increase cost.
In the present embodiment, the mold in step d is preheated to 180 DEG C~230 DEG C.Mold is preheated to 180 DEG C~230 DEG C can be with
The excessive temperature differentials for preventing mold and embryo material avoids the temperature of die surface from being greater than the temperature of mould inside and the temperature on embryo material surface
Degree avoids mold and embryo material from deforming lower than the temperature inside embryo material.
In the present embodiment, blade of aviation engine forging method further includes the steps that the cutting burrs of blade.Blade forging
It is easy residual overlap after the completion of making, influences the quality of blade.It can be protected using edger or laser cutting machine by cutting burrs
Demonstrate,prove the quality of blade.
As shown in Figures 2 and 3, the preferred embodiment of the present invention additionally provide it is a kind of for blade of aviation engine forging
Mold, including the former 1 and formpiston 2 being oppositely arranged, the side of former 1 offers the first extruding slot, the first heading slot and
One finish-forging slot, the side opposite with former 1 of formpiston 2 offer the second extruding slot, the second heading slot and the second finish-forging slot, former
1 is mutually closed with 2 stress of formpiston, so that the first extruding slot and the second extruding slot are mutually closed the extruding to be formed for squeeze bar
Type chamber 3, the first heading slot and the second heading slot are mutually closed the heading type chamber 4 and the first finish-forging slot to be formed for carrying out heading
The finish-forging type chamber 5 to be formed for carrying out finish-forging is mutually closed with the second finish-forging slot, mold further includes for cooperating with extrusion pressing type chamber 3
Squeeze the extruding formed punch 6 of bar and for cooperating the heading formed punch 7 for carrying out heading with heading type chamber 4.Former 1 and formpiston 2 exist
It is mutually closed under the action of equipment, forms extrusion pressing type chamber 3, heading type chamber 4 and finish-forging type chamber 5.When carrying out squeezing bar, embryo material is put
Enter in extrusion pressing type chamber 3, in the elongated forming cavity that embryo material is squeezed into extrusion pressing type chamber 3 under the action of squeezing formed punch 6, is had
The crowded rod piece on head and elongated bar portion.When carrying out heading, the bar portion of crowded rod piece is put into the positioning chamber of heading type chamber 4, is squeezed
The head of rod piece forms tenon under the action of heading formed punch 7, obtains heading part.When carrying out finish-forging, the tenon of heading part is put
The tenon for entering finish-forging type chamber 5 is intracavitary, and former 1 is mutually closed under the action of equipment with formpiston 2, and the bar portion of heading part is pressurized to be formed
Blade and listrium, obtain blade.
As shown in Figures 2 and 3, the first extruding insert 8 is detachably installed in the present embodiment, on former 1, it can on formpiston 2
Disassembly is equipped with the second extruding insert, and the first extruding slot is opened in the first extruding insert 8, and the second extruding slot is opened in second and squeezes
It presses in insert, to be convenient for replacing when first squeezes insert 8 and/or the second extruding insert abrasion.Extrusion pressing type chamber 3 is molding
Squeeze rod piece position, extrusion pressing type chamber 3 due to be squeezed and deformed quick abrasion, be designed to insert structure, first squeeze insert 8 and/or
Second extruding insert is worn up to it cannot be guaranteed that when squeezing the size of rod piece, can be directly taken out the first extruding insert 8 and/or second and be squeezed
Pressure insert is replaced, and the maintenance cost of mold is low.
As shown in Figures 2 and 3, in the present embodiment, the first finish-forging slot is opened in the middle part of former 1, and the second finish-forging slot opens up
In the middle part of formpiston 2, so that the first finish-forging slot and the second finish-forging slot are mutually closed the finish-forging type chamber 5 to be formed and are in mold
Portion, mold is caused former 1 to misplace with formpiston 2 by eccentric force effect when avoiding carrying out finish-forging.Finish-forging type chamber 5 is in mold
When middle part can make heading part carry out finish-forging, the center of effort of heading part is overlapped with the force application center of equipment, avoids mold by inclined
Mental power function causes former 1 to misplace with formpiston 2, improves the vane size accuracy.Optionally, extrusion pressing type chamber 3 is in
The side of mold, heading type chamber 4 are in the other side of the mold far from extrusion pressing type chamber 3.
As shown in Figures 2 and 3, in the present embodiment, the first locating slot, the second finish-forging slot are equipped at the notch of the first finish-forging slot
Notch at be equipped with the second locating slot, to heading when the first locating slot and the second locating slot are mutually closed to be formed for carrying out finish-forging
The bar portion of part is positioned the finish-forging locating slot 9 rolled in finish-forging type chamber 5 to avoid heading part.When carrying out finish-forging, by upsetting
The bar portion of head is placed in finish-forging locating slot 9, can be rolled in finish-forging type chamber 5 to avoid heading part, realizes heading part at end
Accurate positionin in forge chamber 5 avoids blade from occurring being not fully filled defect.
When it is implemented, providing a kind of blade of aviation engine forging method.Below with TC4 titanium alloy blade forging method
For, it is described in detail in the detailed process that blade forging is carried out on horizontal parting horizontal forging and upsetting machine.
1) TC4 titanium alloy embryo material is sawed into 30 × 45 bar of Φ, both ends rounded corner R3.
2) the good TC4 titanium alloy blank of blanking is put into and is heated in the electric furnace that heating temperature is 120 DEG C and keeps the temperature 40min.
3) after soaking time as defined in reaching, TC4 titanium alloy blank is taken out from electric furnace, surface sprays titanium alloy and squeezes
Glass lubricant, coating thickness 0.5mm.
4) blank that will spray glass lubricant is put into and heats in 120 DEG C of electric furnace and keep the temperature 60min.
5) blank is taken out from electric furnace, is transferred to and is heated in the electric furnace that heating temperature is 960 DEG C and keep the temperature 30min.
6) after soaking time as defined in reaching, blank is taken out from electric furnace, is put into the extrusion pressing type chamber 3 of mold, operated
Person steps on the foot pedal that controlled level divides mould horizontal forging and upsetting machine to run, and mold closure squeezes formed punch 6 and is ejected forward, and obtains squeezing rod piece.
7) it squeezes after the completion of bar, mold opens automatically, is removed and placed in crowded rod piece from the extrusion pressing type chamber 3 of mold in 5s
In the heading type chamber 4 of mold, operator depresses foot pedal, mold closure, and heading formed punch 7 is ejected forward, and obtains heading part.
8) after the completion of heading, mold opens automatically, is removed and placed in heading part from the heading type chamber 4 of mold in 5s
In the finish-forging type chamber 5 of mold, operator depresses foot pedal, and mold closure obtains blade.
9) use laser cutting machine by the cutting burrs of blade.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of blade of aviation engine forging method, which comprises the following steps:
A, blanking blanks；
B, in the surface sprayed glass lubricant of embryo material；
C, embryo material is heated to recrystallization temperature or more and kept the temperature；
D, embryo material is put into the extrusion pressing type chamber (3) of preheated mold, carries out squeezing bar, obtain squeezing rod piece；
E, it squeezes after the completion of bar, the crowded rod piece is put into the heading type chamber (4) of the mold in 4s~6s, carry out heading,
Obtain heading part；
F, after the completion of heading, the heading part is put into the finish-forging type chamber (5) of the mold in 4s~6s, carries out finish-forging,
Obtain blade.
2. blade of aviation engine forging method according to claim 1, which is characterized in that
Blanking blanks in the step a specifically: embryo material is sawed into bar, in the both ends rounded corner of bar.
3. blade of aviation engine forging method according to claim 1, which is characterized in that
The surface sprayed glass lubricant in embryo material in the step b specifically: 100 DEG C~120 DEG C at a temperature of heat
Embryo material simultaneously keeps the temperature 30min~60min；In the surface sprayed glass lubricant of embryo material, the coating thickness of glass lubricant is 0.4mm
~0.8mm；Embryo material and 40min~80min is kept the temperature in 100 DEG C~120 DEG C of at a temperature of heating.
4. blade of aviation engine forging method according to claim 1, which is characterized in that
The embryo material uses TC4 titanium alloy embryo material, and the heating temperature in the step c is that TC4 titanium alloy beta phase point temperature subtracts
50 DEG C, soaking time is 1 times~2 times of the diameter of TC4 titanium alloy embryo material.
5. blade of aviation engine forging method according to claim 1, which is characterized in that
Mold in the step d is preheated to 180 DEG C~230 DEG C.
6. blade of aviation engine forging method according to claim 1, which is characterized in that
The blade of aviation engine forging method further includes the steps that the cutting burrs of blade.
7. a kind of mold for blade of aviation engine forging, which is characterized in that
Including the former (1) and formpiston (2) being oppositely arranged, the side of the former (1) offers the first extruding slot, the first heading
Slot and the first finish-forging slot, the formpiston (2) and the former (1) opposite side offer the second extruding slot, the second heading
Slot and the second finish-forging slot,
The former (1) is mutually closed with the formpiston (2) stress, so that described first squeezes slot and the second extruding slot phase
The extrusion pressing type chamber (3), the first heading slot and the second heading slot that mutually closure forms for squeeze bar are mutually closed shape
At for carrying out heading heading type chamber (4) and the first finish-forging slot be mutually closed to be formed with the second finish-forging slot and be used for
The finish-forging type chamber (5) of finish-forging is carried out,
The mold further include for the extrusion pressing type chamber (3) cooperation carry out squeeze bar extruding formed punch (6) and be used for and institute
State the heading formed punch (7) that heading type chamber (4) cooperation carries out heading.
8. the mold according to claim 7 for blade of aviation engine forging, which is characterized in that
First extruding insert (8) is detachably installed on the former (1), second is detachably equipped on the formpiston (2) and is squeezed
Insert is pressed, the first extruding slot is opened in described first and squeezes on insert (8), and the second extruding slot is opened in described second
It squeezes in insert, to be convenient for replacing when described first squeezes insert (8) and/or the second extruding insert abrasion.
9. the mold according to claim 7 for blade of aviation engine forging, which is characterized in that
The first finish-forging slot is opened in the middle part of the former (1), and the second finish-forging slot is opened in the formpiston (2)
Portion, so that the first finish-forging slot and the second finish-forging slot are mutually closed the finish-forging type chamber (5) to be formed and are in the mold
Middle part, the mold is caused the former (1) to misplace with the formpiston (2) by eccentric force effect when avoiding carrying out finish-forging.
10. the mold according to claim 7 for blade of aviation engine forging, which is characterized in that
It is equipped with the first locating slot at the notch of the first finish-forging slot, the second positioning is equipped at the notch of the second finish-forging slot
The bar portion of heading part is carried out when slot, first locating slot and second locating slot are mutually closed to be formed for carrying out finish-forging
Position the finish-forging locating slot (9) rolled in the finish-forging type chamber (5) to avoid the heading part.
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| 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 |
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| 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 |
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| CN109317588A true CN109317588A (en) | 2019-02-12 |
| CN109317588B CN109317588B (en) | 2020-07-24 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110756714A (en) * | 2019-11-10 | 2020-02-07 | 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 |
| CN112275971A (en) * | 2020-08-31 | 2021-01-29 | 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 |
| CN112743021A (en) * | 2020-12-24 | 2021-05-04 | 陕西宏远航空锻造有限责任公司 | Blank making method for forging compressor rotor blade |
| CN116441430A (en) * | 2023-06-19 | 2023-07-18 | 中国航发成都发动机有限公司 | Blade hot extrusion forming device |
| CN116571674A (en) * | 2023-06-20 | 2023-08-11 | 陕西长羽航空装备股份有限公司 | Machining equipment and machining method for aviation aircraft blade |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110756714A (en) * | 2019-11-10 | 2020-02-07 | 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 |
| CN112275971A (en) * | 2020-08-31 | 2021-01-29 | 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 |
| 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 |
| CN112743021A (en) * | 2020-12-24 | 2021-05-04 | 陕西宏远航空锻造有限责任公司 | Blank making method for forging compressor rotor blade |
| CN116441430A (en) * | 2023-06-19 | 2023-07-18 | 中国航发成都发动机有限公司 | Blade hot extrusion forming device |
| 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 |
| CN116571674A (en) * | 2023-06-20 | 2023-08-11 | 陕西长羽航空装备股份有限公司 | Machining equipment and machining method for aviation aircraft blade |
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