CN104308457B - A kind of manufacture method on the square installation limit of aero-engine GH3536 - Google Patents

A kind of manufacture method on the square installation limit of aero-engine GH3536 Download PDF

Info

Publication number
CN104308457B
CN104308457B CN201410404245.0A CN201410404245A CN104308457B CN 104308457 B CN104308457 B CN 104308457B CN 201410404245 A CN201410404245 A CN 201410404245A CN 104308457 B CN104308457 B CN 104308457B
Authority
CN
China
Prior art keywords
rolling
ring base
ring
square
aero
Prior art date
Application number
CN201410404245.0A
Other languages
Chinese (zh)
Other versions
CN104308457A (en
Inventor
张华�
孙传华
杨家典
钟礼彬
陆远贵
兰宝山
张胜利
杨祖建
Original Assignee
贵州航宇科技发展股份有限公司
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 贵州航宇科技发展股份有限公司 filed Critical 贵州航宇科技发展股份有限公司
Priority to CN201410404245.0A priority Critical patent/CN104308457B/en
Publication of CN104308457A publication Critical patent/CN104308457A/en
Application granted granted Critical
Publication of CN104308457B publication Critical patent/CN104308457B/en

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23PMETAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23PMETAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P2700/00Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
    • B23P2700/01Aircraft parts

Abstract

The invention discloses the manufacture method on the square installation limit of a kind of aero-engine GH3536, including blanking, heating, honest thick, punching, rolling etc., wherein: adopting the ring base extruding that rolling is obtained by pressure side's technique is square billet, and adopts the final shaping on saddle support and limit, the saddle side of carrying out, side. Beneficial effects of the present invention: due to bending, uniform wall thickness after base employing rolling, sub-material is accurate, it is ensured that the uniform wall thickness after forging forming, it is possible to reducing design margin, thus saving material, reducing production cost, manufacturing process is relatively easy; By adjusting rolling and saddle support, side's saddle forming parameters, improve product combination property.

Description

A kind of manufacture method on the square installation limit of aero-engine GH3536
Technical field
The present invention relates to the manufacture method on the square installation limit of a kind of aero-engine GH3536.
Background technology
GH3536 alloy is mainly higher by a kind of iron of chromium and molybdenum solution strengthening nickel base superalloy, it is adaptable to manufacturing combustion chamber components and other high-temperature components of aero-engine, less than 900 DEG C life-time service, short-term operation temperature reaches 1080 DEG C. Having good antioxidation and decay resistance, the lasting and creep strength waited until in having below 900 DEG C, hot and cold formability and welding performance are good. GH3536 alloy is mainly for the manufacture of high-temperature components such as the turbo blade of aviation, naval vessels and industrial gas turbine, guide vane, the turbine disk, high-pressure compressor dish and combustor; It is additionally operable to manufacture the conversion equal energy source conversion equipment of aerospace craft, rocket engine, nuclear reactor, petrochemical equipment and coal.
At present, the manufacture method on the square installation limit of aero-engine GH3536 mainly includes, GH3536 square installation limit blank is welded out after being generally adopted free forging process setting down, part is obtained subsequently through machining, the shortcoming of employing said method is: welding after adopting setting down, manufacture process is complicated, and pad intensity is not enough, defect easily occurs, affects the combination property of final products; Owing to subsequent mechanical processes pre-made allowance relatively greatly, processing cost is high.
Summary of the invention
It is an object of the invention to provide the manufacture method on the square installation limit of a kind of aero-engine GH3536, solve the problems such as current aero-engine GH3536 square installation manufacturing process is complicated, product combination property is poor, production cost is high.
For solving above-mentioned technical problem, the present invention is achieved by the following technical solutions:
The manufacture method on the square installation limit of a kind of aero-engine GH3536, including blanking, heating, honest thick, punching, rolling etc., wherein: adopting the ring base that rolling is obtained by pressure side technique to extrude is square billet, mainly comprises the steps that
(1) blanking, heating, honest thick, punching
By GH3536 alloy blank chamfering R20mm, adopting heating-up temperature to be 1100 DEG C��1170 DEG C and blank is heated, the heating and thermal insulation time calculates according to 6min/10mm;It is the 21%��24% of raw footage by blank jumping-up vertically to length, is punched out with drift;
(2) rolling
Being melted down by ring base A after reheating, load machine for rolling ring and roll, the home roll rotating speed of looping mill is 1.5rad/s, and cone roller rotating speed is 1.0rad/s; Feed rate of idle roll is increased to 0.8mm/s by 0mm/s, makes ring base A nip rolling; Again feed rate of idle roll is increased to 1.8mm/s by 0.8mm/s, make ring base A stable rolling; Again feed rate of idle roll is gradually decreased to 0mm/s by 1.8mm/s, thus obtaining the ring base B being of the required size;
(3) pressure side
Ring base B is melted down after reheating, in described ring base B endoporus, put into mould, described mould is put on a hydraulic press together with ring base B, and respectively in order from direction A, direction B, direction C, direction D extrusion ring base B, it is thus achieved that meet the square billet of dimensional requirement;
(4) shape
Being melted down by square billet after reheating, use saddle support, side's saddle to shape on a hydraulic press, obtain described square installation limit, the forging pressure of hydraulic press described in forming process is 820T, and pressing speed under described hydraulic press is 12mm/s.
Preferably, in step (2), the roll-force of machine for rolling ring is 170T��198T.
Beneficial effects of the present invention: the invention provides the manufacture method on the square installation limit of a kind of aero-engine GH3536, due to bending after base employing rolling, uniform wall thickness, sub-material is accurate, ensure that the uniform wall thickness after forging forming, it is possible to reduce design margin, thus saving material, reducing production cost, manufacturing process is relatively easy; By adjusting rolling and saddle support, side's saddle forming parameters, improve product combination property.
Accompanying drawing explanation
Fig. 1 is GH3536 alloy blank figure
Fig. 2 is the ring base figure after earnestly thick, the punching of GH3536 alloy blank
Fig. 3 is the ring base figure after Fig. 2 passes through rolling
Fig. 4 is square billet figure
Fig. 5 is the square installation limit part drawing after shaping
Fig. 6 is rolling schematic diagram
Fig. 7 is pressure side's schematic diagram
Fig. 8 is extruding rear mold and square billet state diagram
Fig. 9 shapes schematic diagram for using saddle support and side's saddle
Figure 10 is the A-A profile of Fig. 9
In figure, 1 blank, 2 ring base A, 3 ring base B, 4 square billets, 5 square installation limits, 6 home rolls, 7 core rollers, 8 moulds, 9 direction A, 10 direction B, 11 direction C, 12 direction D, 13 hydraulic presses, 14 side's saddles, 15 saddle supports
Detailed description of the invention
For making the object, technical solutions and advantages of the present invention clearly, below in conjunction with the drawings and Examples of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that, described embodiment is a part of embodiment of the present invention, rather than whole embodiments. Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of protection of the invention.
The manufacture method implementing the square installation limit of a kind of aero-engine GH3536 of the present invention needs to provide the equipment such as forge furnace, forcing press, machine for rolling ring, mechanical hand and other moulds of industrial equipment.
The main chemical elements content (percentage by weight) of this alloy is: C content 0.05%��0.15%, 20.5%��23% is measured containing Cr, 0.5%��2.5% is measured containing Co, 0.2%��1.0% is measured containing W, 8.0%��10.0% is measured containing Mo, 17.0%��20.0% is measured containing Fe, �� 0.50% is measured containing Al, �� 0.15% is measured containing Ti, the amount containing Cu is 0.50%, �� 1.0% is measured containing Mn, �� 0.015% is measured containing S, P content��0.025%, �� 0.01% is measured containing B, si content��1.0%, all the other are Ni.
As shown in accompanying drawing 1 to Figure 10, the manufacture method on the square installation limit of a kind of aero-engine GH3536, including blanking, heating, honest thick, punching, rolling etc., wherein: adopting the ring base that rolling is obtained by pressure side technique to extrude is square billet, mainly comprise the steps that
(1) blanking, heating, honest thick, punching
By GH3536 alloy blank 1 chamfering R20mm, adopting heating-up temperature to be 1100 DEG C��1170 DEG C and blank is heated, the heating and thermal insulation time calculates according to 6min/10mm; It is the 21%��24% of raw footage by blank 1 jumping-up vertically to length, is punched out with drift;
(2) rolling
Being melted down by ring base A2 after reheating, load machine for rolling ring and roll, home roll 6 rotating speed of looping mill is 1.5rad/s, and cone roller (attached not shown in FIG.) rotating speed is 1.0rad/s; Core roller 7 feed speed is increased to 0.8mm/s by 0mm/s, makes ring base A2 nip rolling; Again core roller 7 feed speed is increased to 1.8mm/s by 0.8mm/s, make ring base A2 stable rolling; Again core roller 7 feed speed is gradually decreased to 0mm/s by 1.8mm/s, thus obtaining the ring base B3 being of the required size;
(3) pressure side
Ring base B3 is melted down after reheating, described ring base B3 endoporus puts into mould 8, described mould 8 is put on a hydraulic press together with ring base B3, and respectively in order from direction A9, direction B10, direction C11, direction D12 extrusion ring base B3, it is thus achieved that meet the square billet 4 of dimensional requirement;
(4) shape
Being melted down by square billet 4 after reheating, use saddle support 15, side's saddle 14 to shape, obtain described square installation limit 5 on hydraulic press 13, the forging pressure of hydraulic press 13 described in forming process is 820T, and the pressure speed down of described hydraulic press 13 is 12mm/s.
In above-mentioned steps (2), the roll-force of machine for rolling ring is 170T��198T.
By the forging that said method obtains, its mechanical property is: room temperature tensile (longitudinal direction): RmFor 700MPa��750MPa, Rp0.2For 330MPa��355MPa, ��5It is 48%; Brinell hardness is 179HBW; Lasting 815 DEG C of (longitudinal direction): the �� of high temperature are 105MPa, �� is 98%��102%, and T is 33.1h��33.5h, and above technical specification has exceeded technical standard (HB5496-1992) requirement.
Above example only in order to technical scheme to be described, is not intended to limit; Although the present invention being described in detail with reference to previous embodiment, it will be understood by those within the art that: the technical scheme described in previous embodiment still can be modified by it, or wherein some or all of technical characteristic is carried out equivalent replacement; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the scope of embodiment of the present invention technical scheme.

Claims (2)

1. the manufacture method on the square installation limit of aero-engine GH3536, including blanking, heating, honest thick, punching, rolling, it is characterised in that: adopting the ring base that rolling is obtained by pressure side technique to extrude is square billet, mainly comprises the steps that
(1) blanking, heating, honest thick, punching
By GH3536 alloy blank (1) chamfering R20mm, adopting heating-up temperature to be 1100 DEG C��1170 DEG C and blank is heated, the heating and thermal insulation time calculates according to 6min/10mm; It is the 21%��24% of raw footage by blank (1) jumping-up vertically to length, is punched out with drift;
(2) rolling
Being melted down by ring base A (2) after reheating, load machine for rolling ring and roll, the home roll rotating speed of machine for rolling ring is 1.5rad/s, and cone roller rotating speed is 1.0rad/s;Feed rate of idle roll is increased to 0.8mm/s by 0mm/s, makes ring base A (2) nip rolling; Again feed rate of idle roll is increased to 1.8mm/s by 0.8mm/s, make ring base A (2) stable rolling; Again feed rate of idle roll is gradually decreased to 0mm/s by 1.8mm/s, thus obtaining ring base B (3) being of the required size;
(3) pressure side
Ring base B (3) is melted down after reheating, described ring base B (3) endoporus puts into mould (8), described mould (8) and ring base B (3) are put on a hydraulic press together, and respectively in order from direction A (9), direction B (10), direction C (11), direction D (12) extrusion ring base B (3), it is thus achieved that meet the square billet (4) of dimensional requirement;
(4) shape
Square billet (4) is melted down after reheating, hydraulic press (13) use saddle support (15), side's saddle (14) shape, obtain described square installation limit (5), the forging pressure of hydraulic press described in forming process (13) is 820T, and the pressure speed down of described hydraulic press (13) is 12mm/s.
2. the manufacture method on the square installation limit of aero-engine GH3536 as claimed in claim 1, it is characterised in that: in step (2), the roll-force of machine for rolling ring is 170T��198T.
CN201410404245.0A 2014-08-18 2014-08-18 A kind of manufacture method on the square installation limit of aero-engine GH3536 CN104308457B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201410404245.0A CN104308457B (en) 2014-08-18 2014-08-18 A kind of manufacture method on the square installation limit of aero-engine GH3536

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201410404245.0A CN104308457B (en) 2014-08-18 2014-08-18 A kind of manufacture method on the square installation limit of aero-engine GH3536

Publications (2)

Publication Number Publication Date
CN104308457A CN104308457A (en) 2015-01-28
CN104308457B true CN104308457B (en) 2016-06-08

Family

ID=52363840

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201410404245.0A CN104308457B (en) 2014-08-18 2014-08-18 A kind of manufacture method on the square installation limit of aero-engine GH3536

Country Status (1)

Country Link
CN (1) CN104308457B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107030247A (en) * 2017-06-21 2017-08-11 山东南山铝业股份有限公司 Special-shaped saddle, the processing unit (plant) and method for installing side

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0906798A2 (en) * 1997-10-01 1999-04-07 General Motors Corporation Method of manufacturing a reservoir tube
CN1668401A (en) * 2002-07-12 2005-09-14 三菱麻铁里亚尔株式会社 Frame producing method and frame
CN1695847A (en) * 2004-05-11 2005-11-16 古河Sky株式会社 Mfg.method of multi-side section ducted body and said body
CN101279347A (en) * 2008-04-23 2008-10-08 贵州航宇科技发展有限公司 Method for rolling and shaping stainless steel conical ring
CN101279344A (en) * 2008-04-23 2008-10-08 贵州安大航空锻造有限责任公司 Method for rolling and shaping aluminum alloy special-shaped ring forging

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07106418B2 (en) * 1993-07-30 1995-11-15 大島機工株式会社 Precision square long hole processing method and processed product

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0906798A2 (en) * 1997-10-01 1999-04-07 General Motors Corporation Method of manufacturing a reservoir tube
CN1668401A (en) * 2002-07-12 2005-09-14 三菱麻铁里亚尔株式会社 Frame producing method and frame
CN1695847A (en) * 2004-05-11 2005-11-16 古河Sky株式会社 Mfg.method of multi-side section ducted body and said body
CN101279347A (en) * 2008-04-23 2008-10-08 贵州航宇科技发展有限公司 Method for rolling and shaping stainless steel conical ring
CN101279344A (en) * 2008-04-23 2008-10-08 贵州安大航空锻造有限责任公司 Method for rolling and shaping aluminum alloy special-shaped ring forging

Also Published As

Publication number Publication date
CN104308457A (en) 2015-01-28

Similar Documents

Publication Publication Date Title
CN104438419B (en) A kind of forging molding process of high tubular aluminum alloy forge piece
CN103894436B (en) A kind of reciprocating extrusion device and processing method strengthening magnesium-alloy tube
CN102615223B (en) The method of rolling two trapezoid cross section flange ring forging parts simultaneously
CN105107915B (en) Technological method for precise spinning forming of large magnesium alloy thin-walled cylindrical part
CN102319992B (en) Method for manufacturing aluminum alloy die forging
CN102205482B (en) Method for producing round-link chain
CN100482830C (en) Aviation aluminum alloy pre-stretching plate and production method thereof
CN104826890A (en) Manufacturing method of super austenitic stainless steel seamless tube
CN104722702B (en) Supercritical unit high temperature steam pipeline forging molding process
CN102644039B (en) Preparation method of high-quality 6061 aluminium alloy forging for semiconductor equipment
CN104561696B (en) High ferro 5083 aluminum alloy plate materials and production method thereof
CN104759850B (en) A kind of aluminium alloy height barrier part processing technique
CN102240774B (en) Fine forging forming method of spiral bevel gears
CN101733348B (en) Isothermal forging method for titanium alloy blade
CN104099539B (en) A kind of manufacture method of long fibre concrete dynamic modulus metal material
CN101398165B (en) Major vapour inlet/outlet joint pipe for nuclear plant steam generator and forging method thereof
CN103128102B (en) Production method of titanium alloy oil well pipe
CN103691855B (en) The roll forming of structural steel straight-flanked ring base is the method for special-shaped thin wall ring
CN100506422C (en) Flange of wind power generation tower barrel forging shaping process
EP3036053B1 (en) Process for producing a multilayer pipe having a metallurgical bond by drawing
CN101439350B (en) Method for producing seamless steel pipe for producing gas cylinder with heavy caliber for hauled vehicle
CN103894792B (en) Method for machining forge piece of large-scale single-flange anti-explosion motor main shaft of all-fiber texture
CN102689151B (en) Liquid die forging and rolling compound formation method for GH4033 high-temperature alloy irregular-section large ring piece
CN104060203B (en) A kind of production technique of alloy extrusion bar
CN101502872A (en) Shortened method for producing oxygen-free copper belt

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant
PE01 Entry into force of the registration of the contract for pledge of patent right
PE01 Entry into force of the registration of the contract for pledge of patent right

Denomination of invention: Manufacturing method of GH3536 square mounting edges for aero-engine

Effective date of registration: 20171127

Granted publication date: 20160608

Pledgee: Bank of Guiyang Limited by Share Ltd high tech branch

Pledgor: Guizhou Aviation Technical Development Co., Ltd.

Registration number: 2017990001066

Denomination of invention: Manufacturing method of GH3536 square mounting edges for aero-engine

Effective date of registration: 20171127

Granted publication date: 20160608

Pledgee: Bank of Guiyang Limited by Share Ltd high tech branch

Pledgor: Guizhou Aviation Technical Development Co., Ltd.

Registration number: 2017990001066

PC01 Cancellation of the registration of the contract for pledge of patent right
PC01 Cancellation of the registration of the contract for pledge of patent right

Date of cancellation: 20200924

Granted publication date: 20160608

Pledgee: Bank of Guiyang Limited by Share Ltd. high tech branch

Pledgor: Guizhou Aviation Technical Development Co.,Ltd.

Registration number: 2017990001066

PE01 Entry into force of the registration of the contract for pledge of patent right
PE01 Entry into force of the registration of the contract for pledge of patent right

Denomination of invention: A manufacturing method of GH3536 square mounting edge for Aeroengine

Effective date of registration: 20200930

Granted publication date: 20160608

Pledgee: Guanshanhu sub branch of Guiyang Bank Co., Ltd

Pledgor: Guizhou Aviation Technical Development Co.,Ltd.

Registration number: Y2020520000015