CN101761542A - Large integral disc-shaft forging piece formed by similar isothermal forging - Google Patents
Large integral disc-shaft forging piece formed by similar isothermal forging Download PDFInfo
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- CN101761542A CN101761542A CN200910102899A CN200910102899A CN101761542A CN 101761542 A CN101761542 A CN 101761542A CN 200910102899 A CN200910102899 A CN 200910102899A CN 200910102899 A CN200910102899 A CN 200910102899A CN 101761542 A CN101761542 A CN 101761542A
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Abstract
The invention discloses a large integral disc-shaft forging piece formed by similar isothermal forging, which solves the technical problems that the forging piece is rapidly formed when in forging and high-precision size and good texture and performance are obtained; the forging piece comprises a disc body and a shaft neck body, a transition region is arranged at the connecting part between the disc body and the shaft neck body, the center of the top disc surface of the disc body is provided with an upper locating blind hole matched with an upper locating block of a forging mold for forging the forging piece, and the center of the bottom surface of the shaft neck body is provided with a lower locating blind hole matched with a lower locating block of the forging mold; the dimensional proportion of the forging piece is that: when t1:t2:t3:h1:h3 is equal to 1:2:5:3.5:2.5, and d4:d2:d6:d5:d3:d1 is equal to 1:1.5:2:3.5:1.6:5, the structure is optimal. The forging piece is mainly used for the large integral disc-shaft forging pieces which are formed integrally, such as compressor discs and front shaft necks of aircraft engines.
Description
Technical field
The present invention relates to a kind of forging, particularly the large integral disc forging shaft of near isothermal forging shaping.
Background technique
The compressor disc of aeroengine and with the large forgings such as preceding axle journal of its assembling because work under bad environment, stressed complexity requires forging will have the excellent comprehensive performance.Some aeroengine of current domestic development and production, its compressor disc and preceding axle journal fit together after adopting split to forge again, three grades of compressor discs as certain aeroengine adopt the TC17 titanium alloy forging, preceding axle journal adopts the TC4 titanium alloy forging, compressor disc and preceding axle journal is fitted together with bolt again.Adopt this split type dish axle builtup member, process-cycle and cost have not only been increased, reduced productivity, be difficult for maintaining, and, be unfavorable for realizing engine structure loss of weight and the reliability and the life-span of improving thrust weight ratio, being unfavorable for improving engine structure because of adopting Bolt Connection to increase the weight of motor.Therefore, people attempt to take integrally formed method that above-mentioned dish axle builtup member forging is integral, but require to come to an end because of be shaped difficulty and tissue, performance reach eventually.The appearance of nearly isothermal forging technology makes described dish axle builtup member forge to be integral becomes possibility, when adopting nearly isothermal forging unitary moulding, the structural design of forging with manufactured the key that can realize quick shaping and obtain the integral disc-shaft spare of excellent tissue, performance.
Summary of the invention
The technical problem to be solved in the present invention provides the integral disc-shaft forging that a kind of near isothermal forging with positioning hole is shaped, and this forging is easy to realize quick shaping when near isothermal forging, forging ' s block dimension precision height, tissue and excellent performance.
For solving the problems of the technologies described above, the large integral disc forging shaft that near isothermal forging of the present invention is shaped, comprise disking body and journal body, the position that joins between described disking body and journal body is provided with transition zone, described disking body take over a business the face center have cooperate with positioning block on the forging die that is used to forge this forging on locate blind hole, have the following location blind hole that cooperates with the following positioning block of described forging die in the bottom center of described journal body.
The dimension scale of described forging is:
t
1∶t
2∶t
3∶h
1∶h
3＝1∶2∶5∶3.5∶2.5
Wherein, t
1Be the thickness of described disking body, t
2Be the thickness of described transition zone, t
3Be the thickness of described journal body, h
1Be the described height of going up the location blind hole, h
3It is the height of described location down blind hole;
And d
4: d
2: d
6: d
5: d
3: d
1=1: 1.5: 2: 3.5: 1.6: 5
Wherein, d
4Be the diameter of described location down blind hole, d
2Be the following conical surface diameter of described journal body, d
6The following conical surface diameter that is described transition zone also is the last conical surface diameter of described journal body, d
5Be the last conical surface diameter of described transition zone, d
3Be the described diameter of going up the location blind hole, d
1It is the diameter of described disking body.
Compared with prior art, beneficial effect of the present invention is as follows:
The large integral disc forging shaft that near isothermal forging of the present invention is shaped is provided with transition zone by the position that joins between described forging disking body and journal body, the disking body and the journal body that make original difficulty be configured as one become more or less freely when global formation; Described disking body take over a business the face center be provided with cooperate with positioning block on the forging die on locate blind hole, bottom center in described journal body is provided with the following location blind hole that cooperates with the following positioning block of forging die, described forging is positioned in the described forging die by complete closed and coaxial line, realize the forging quick shaping, obtained the large integral disc forging shaft of dimensional accuracy height and tissue, excellent performance.
The dimension scale of particularly working as described forging: t
1: t
2: t
3: h
1: h
3=1: 2: 5: 3.5: 2.5 and d
4: d
2: d
6: d
5: d
3: d
1=1: 1.5: 2: 3.5: 1.6: 5 o'clock, be the preferential project organization of the best, be easier to realize quick shaping and obtain high dimension precision and excellent tissue, performance.
The large integral disc forging shaft that is shaped with TC17 titanium alloy near isothermal forging is an example, and forging after heat treatment its each position has obtained comparatively ideal basket with netting on top tissue and high-performance.
The room temperature tensile performance at this each position of alloy material integral disc-shaft forging after testing, specific as follows:
Disking body position for this forging: tensile strength is 1180MPa～1190MPa (greater than the 1120MPa of design usage requirement), its elongation percentage is that 0.2% o'clock yield strength is 1150MPa (greater than the 1030MPa of design usage requirement), elongation after fracture be 10%～14% (greater than the design usage requirement 5%), reduction of cross sectional area be 23%～29% (greater than the design usage requirement 10%), fracture toughness is 66Mpa.m1/2 (greater than the 54.9Mpa.m1/2 of design usage requirement).
Transition zone position for this forging: tensile strength is 1130MPa～1150MPa (greater than the 1120MPa of design usage requirement), its elongation percentage is that 0.2% o'clock yield strength is 1110MPa (greater than the 1030MPa of design usage requirement), elongation after fracture be 13%～15% (greater than the design usage requirement 5%), reduction of cross sectional area be 33% (greater than the design usage requirement 10%), fracture toughness is 76Mpa.m1/2 (greater than the 54.9Mpa.m1/2 of design usage requirement).
For this forging journal body position: tensile strength is 1160MPa～1180MPa (greater than the 1120MPa of design usage requirement), its elongation percentage is that 0.2% o'clock yield strength is 1130MPa～1150MPa (greater than the 1030MPa of design usage requirement), elongation after fracture be 7.0%～9.5% (greater than the design usage requirement 5%), reduction of cross sectional area be 12%～16% (greater than the design usage requirement 10%), fracture toughness is 68Mpa.m1/2 (greater than the 54.9Mpa.m1/2 of design usage requirement).
Description of drawings
Below in conjunction with the drawings and specific embodiments the present invention is described in further detail.
Fig. 1 is the vertical section structure figure of the large integral disc forging shaft of near isothermal forging shaping along its center line.
The phase diagram of forging die location forging when Fig. 2 is nearly isothermal forging.
Fig. 3 is forging shown in Figure 1 is vertically cut its disking body position, back when adopting the TC17 titanium alloy open along center line metallographic structure figure.
Fig. 4 is forging shown in Figure 1 is vertically cut its transition zone position, back when adopting the TC17 titanium alloy open along center line metallographic structure figure.
Fig. 5 is forging shown in Figure 1 is vertically cut its journal body position, back when adopting the TC17 titanium alloy open along center line metallographic structure figure.
Embodiment
Fig. 1 shows the vertical section structure of the large integral disc forging shaft of near isothermal forging shaping along its center line, and the top of this integral disc-shaft forging is disking body 1, and its underpart is a journal body 3, and the position that joins between disking body 1 and journal body 3 is a transition zone 2.Described disking body 1 take over a business the face center have toroidal on the location blind hole 2
b, the diameter of this blind hole is d
3, the inclination angle is d, highly is h
1The following location blind hole 3 that has toroidal in the bottom center of described journal body 3
a, the radius of this blind hole is d
4, the inclination angle is β, highly is h
3Wherein the diameter of disking body 1 is d
1, thickness is t
1Transition zone 2 is a taper structure, and conical surface diameter is d on it
5, down conical surface diameter is d
6, its thickness is t
2Journal body 3 is a taper structure, and conical surface diameter is d on it
6, down conical surface diameter is d
2, its thickness is t
3
Fig. 2 shows the state when adopting forging die near isothermal forging large integral disc forging shaft, forges when finishing the last positioning block 10 of last forging die 10
bLocate blind hole 2 with going up of described large integral disc forging shaft
bCooperate the following positioning block 20 of anvil tool 20 fully
aFollowing location blind hole 3 with described large integral disc forging shaft
aCooperate fully, described forging is positioned in the described forging die by complete closed and coaxial line, has realized quick shaping.
Size t when above-mentioned integral disc-shaft forging
1: t
2: t
3: h
1: h
3=1: 2: 5: 3.5: 2.5 and d
4: d
2: d
6: d
5: d
3: d
1=1: 1.5: 2: 3.5: 1.6: 5 o'clock, this forging was easier to realize quick shaping and obtains excellent tissue and performance, is example with the titanium alloy large-sized integral disc-shaft forging of near isothermal forging TC17, and forging its tissue and performance after solid solution+timeliness heat treatment is as follows:
When adopting the TC17 titanium alloy material for integral disc-shaft forging shown in Figure 1, Fig. 3 vertically cuts the metallographic structure figure (microscopically amplifies 500 times) at its disking body 1 position, back open along center line, the α bar is a fine acicular, most of α bar Elongation＞10, be evenly distributed and be the blue braiding of net shape and arrange, crystal boundary is broken and thinner.
When adopting the TC17 titanium alloy material for integral disc-shaft forging shown in Figure 1, Fig. 4 vertically cuts the metallographic structure figure (microscopically amplifies 500 times) at its transition zone 2 positions, back open along center line, the α bar is a fine acicular, most of α bar Elongation＞10, be evenly distributed and be the blue braiding of net shape and arrange, crystal boundary is broken and thinner.
When adopting the TC17 titanium alloy material for integral disc-shaft forging shown in Figure 1, Fig. 5 vertically cuts the metallographic structure figure (microscopically amplifies 500 times) at its journal body 3 positions, back open along center line, the α bar is a fine acicular, most of α bar Elongation＞10, be evenly distributed and be the blue braiding of net shape and arrange, crystal boundary is broken and thinner.
From Fig. 3, Fig. 4 and Fig. 5 as can be seen, adopt each position even tissue unanimity of integral disc-shaft forging of TC17 titanium alloy near isothermal forging.
After testing, the room temperature tensile performance at each position of integral disc-shaft forging of employing TC17 titanium alloy material near isothermal forging is as follows:
For disking body 1: tensile strength is 1180MPa～1190MPa, and its elongation percentage is that 0.2% o'clock yield strength is 1150MPa, and elongation after fracture is 10%～14%, and reduction of cross sectional area is 23～29%, and fracture toughness is 66Mpa.m1/2.
For transition zone 2: tensile strength is 1130MPa～1150MPa, and its elongation percentage is that 0.2% o'clock yield strength is 1110MPa, and elongation after fracture is 13%～15%, and reduction of cross sectional area is 33%, and fracture toughness is 76Mpa.m1/2.
For journal body 3: tensile strength is 1160MPa～1180MPa, and its elongation percentage is that 0.2% o'clock yield strength is 1130MPa～1150MPa, and elongation after fracture is 7.0%～9.5%, and reduction of cross sectional area is 12%～16%, and fracture toughness is 68Mpa.m1/2.
Claims (2)
1. the large integral disc forging shaft that is shaped of a near isothermal forging, comprise disking body and journal body, it is characterized in that: the position that joins between described disking body and journal body is provided with transition zone, described disking body take over a business the face center have cooperate with positioning block on the forging die that is used to forge this forging on locate blind hole, have the following location blind hole that cooperates with the following positioning block of described forging die in the bottom center of described journal body.
2. large integral disc forging shaft according to claim 1 is characterized in that, the dimension scale of described forging is:
t
1∶t
2∶t
3∶h
1∶h
3＝1∶2∶5∶3.5∶2.5
Wherein, t
1Be the thickness of described disking body, t
2Be the thickness of described transition zone, t
3Be the thickness of described journal body, h
1Be the described height of going up the location blind hole, h
3It is the height of described location down blind hole;
And d
4: d
2: d
6: d
5: d
3: d
1=1: 1.5: 2: 3.5: 1.6: 5
Wherein, d
4Be the diameter of described location down blind hole, d
2Be the following conical surface diameter of described journal body, d
6The following conical surface diameter that is described transition zone also is the last conical surface diameter of described journal body, d
5Be the last conical surface diameter of described transition zone, d
3Be the described diameter of going up the location blind hole, d
1It is the diameter of described disking body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101028997A CN101761542B (en) | 2009-11-27 | 2009-11-27 | Large integral disc-shaft forging piece formed by similar isothermal forging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101028997A CN101761542B (en) | 2009-11-27 | 2009-11-27 | Large integral disc-shaft forging piece formed by similar isothermal forging |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101761542A true CN101761542A (en) | 2010-06-30 |
| CN101761542B CN101761542B (en) | 2011-11-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009101028997A Active CN101761542B (en) | 2009-11-27 | 2009-11-27 | Large integral disc-shaft forging piece formed by similar isothermal forging |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104061386A (en) * | 2014-06-17 | 2014-09-24 | 德清恒丰机械有限公司 | Automotive flange forging piece |
| CN104061388A (en) * | 2014-06-19 | 2014-09-24 | 德清恒丰机械有限公司 | Novel flange forge piece for automobile |
| CN104108012A (en) * | 2014-07-28 | 2014-10-22 | 中国南方航空工业(集团)有限公司 | Forging method of disc-shaped integrated part and die used for forging method |
| CN106493282A (en) * | 2016-12-01 | 2017-03-15 | 贵州安大航空锻造有限责任公司 | Ti1023 titanium alloy tubular journal forging near isothermal forging manufacturing process |
| CN106694788A (en) * | 2016-12-01 | 2017-05-24 | 贵州安大航空锻造有限责任公司 | GH4169 alloy hollow shaft neck forged piece nearly-isothermal forging forming method |
| CN115121751A (en) * | 2022-06-27 | 2022-09-30 | 中国航发北京航空材料研究院 | Forming method of nickel-based high-temperature alloy hollow turbine disc shaft integrated forging |
-
2009
- 2009-11-27 CN CN2009101028997A patent/CN101761542B/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104061386A (en) * | 2014-06-17 | 2014-09-24 | 德清恒丰机械有限公司 | Automotive flange forging piece |
| CN104061388A (en) * | 2014-06-19 | 2014-09-24 | 德清恒丰机械有限公司 | Novel flange forge piece for automobile |
| CN104108012A (en) * | 2014-07-28 | 2014-10-22 | 中国南方航空工业(集团)有限公司 | Forging method of disc-shaped integrated part and die used for forging method |
| CN106493282A (en) * | 2016-12-01 | 2017-03-15 | 贵州安大航空锻造有限责任公司 | Ti1023 titanium alloy tubular journal forging near isothermal forging manufacturing process |
| CN106694788A (en) * | 2016-12-01 | 2017-05-24 | 贵州安大航空锻造有限责任公司 | GH4169 alloy hollow shaft neck forged piece nearly-isothermal forging forming method |
| CN115121751A (en) * | 2022-06-27 | 2022-09-30 | 中国航发北京航空材料研究院 | Forming method of nickel-based high-temperature alloy hollow turbine disc shaft integrated forging |
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| Publication number | Publication date |
|---|---|
| CN101761542B (en) | 2011-11-02 |
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