CN114277221A - Method for improving flaw detection quality of X22CrMoV12-1 disk of gas turbine - Google Patents
Method for improving flaw detection quality of X22CrMoV12-1 disk of gas turbine Download PDFInfo
- Publication number
- CN114277221A CN114277221A CN202111550573.8A CN202111550573A CN114277221A CN 114277221 A CN114277221 A CN 114277221A CN 202111550573 A CN202111550573 A CN 202111550573A CN 114277221 A CN114277221 A CN 114277221A
- Authority
- CN
- China
- Prior art keywords
- forging
- forge piece
- piece
- flaw detection
- x22crmov12
- 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.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 34
- 238000001514 detection method Methods 0.000 title claims abstract description 32
- 238000005242 forging Methods 0.000 claims abstract description 65
- 238000001816 cooling Methods 0.000 claims abstract description 30
- 238000005496 tempering Methods 0.000 claims abstract description 20
- 238000010438 heat treatment Methods 0.000 claims abstract description 18
- 238000010791 quenching Methods 0.000 claims abstract description 17
- 230000000171 quenching effect Effects 0.000 claims abstract description 17
- 238000007599 discharging Methods 0.000 claims abstract description 6
- 239000002994 raw material Substances 0.000 claims abstract description 5
- 238000004321 preservation Methods 0.000 claims description 11
- 238000012545 processing Methods 0.000 claims description 4
- 230000035945 sensitivity Effects 0.000 abstract description 7
- 238000003754 machining Methods 0.000 abstract description 2
- 239000013078 crystal Substances 0.000 description 8
- 230000008569 process Effects 0.000 description 6
- 229910001220 stainless steel Inorganic materials 0.000 description 3
- 239000010935 stainless steel Substances 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 229910000734 martensite Inorganic materials 0.000 description 1
- 229910001105 martensitic stainless steel Inorganic materials 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Images
Landscapes
- Forging (AREA)
Abstract
The invention discloses a method for improving the flaw detection quality of an X22CrMoV12-1 disk part of a gas turbine, which comprises the following steps: step S1: preparing a forging raw material; step S2: carrying out re-forging on the forge piece, wherein the re-forging comprises upsetting and drawing out; step S3: the forge piece is returned to the furnace and is insulated, the forge piece is upset, and the deformation of the forge piece is controlled to be 50 percent; step S4: performing heat treatment after forging, namely, putting a forged piece into a furnace, heating the forged piece to 960-980 ℃, preserving heat, then cooling the forged piece to 760-770 ℃, preserving heat, and finally, cooling the forged piece to below 650 ℃ in the furnace and discharging the forged piece; step S5: quenching the forge piece, wherein the quenching temperature range is 1017-1024 ℃, the temperature of the forge piece is kept for 3-7 h, and the forge piece is cooled to the room temperature; step S6: tempering the forge piece, wherein the tempering temperature range is 683-707 ℃, the heat of the forge piece is preserved for 4-9 h, and the forge piece is cooled to room temperature; step S7: rough machining of forgings and UT flaw detection, the invention has the advantages that grains in all directions after forging are ensured to be as fine as possible, the inheritance of the grains is cut off through reasonable heat treatment after forging, and the grains in all directions can obtain fine grains, so that the grain size meets the requirement of flaw detection sensitivity of 0.5 mm.
Description
Technical Field
The invention relates to the field of stainless steel forging, in particular to a method for improving the flaw detection quality of an X22CrMoV12-1 disk part of a gas turbine.
Background
The compressor disk is an important part in a gas turbine, works under the conditions of high rotating speed and high temperature, bears large and complex stress in a working state, and needs a forged piece to have higher tensile property, durability and fatigue property, and the indexes are closely related to the purity of the forged piece. At present, the compressor disk is made of X22CrMoV12-1 martensitic stainless steel, and the stainless steel has good hardenability, hardness of quenching and tempering, wear resistance and strength. With the development of the technology, the compressor disk has higher performance requirements. The outer diameter of the existing compressor disk is 800mm-1000mm, the sensitivity of 0.5mm needs to penetrate through the whole outer diameter, and the requirement on the radial grain size of a forged piece is very high.
The heat treatment process of the stainless steel at present comprises the following steps: the method comprises the steps of forging an X22CrMoV12-1 electroslag ingot, then forming to a required size after the forging process is changed to be normal, tempering at high temperature of 760 ℃, oil cooling by 1020 quenching, tempering at 680 and roughly processing an UT flaw detection die. According to the traditional process, the radial grain size of the forge piece is only about 3 grades, UT flaw detection is carried out from the excircle after rough machining, and the sensitivity can only reach 1.5 mm. Because the grain size of the X22CrMoV12-1 martensite heat-resistant steel has heredity, if fine grains can not be obtained by forging, the heredity can not be cut off by normal quenching and tempering, so that the traditional process can not meet the design requirement of the sensitivity of flaw detection of 0.5 mm.
Disclosure of Invention
In view of the defects of the prior art, the invention aims to provide a method for improving the flaw detection quality of an X22CrMoV12-1 disk of a gas turbine, which has the advantages that grains in all directions after forging are ensured to be as fine as possible, the inheritance of the grains is cut off through reasonable heat treatment after forging, and the grains in all directions can obtain fine grains, so that the grain size meets the requirement of 0.5mm flaw detection sensitivity.
The technical purpose of the invention is realized by the following technical scheme:
a method for improving the flaw detection quality of an X22CrMoV12-1 disk of a gas turbine comprises the following steps:
step S1: preparing a forging raw material;
step S2: carrying out re-forging on the forge piece, wherein the re-forging comprises upsetting and drawing out;
step S3: the forge piece is returned to the furnace and is insulated, the forge piece is upset, and the deformation of the forge piece is controlled to be 50 percent;
step S4: performing heat treatment after forging, namely, putting a forged piece into a furnace, heating the forged piece to 960-980 ℃, preserving heat, then cooling the forged piece to 760-770 ℃, preserving heat, and finally, cooling the forged piece to below 650 ℃ in the furnace and discharging the forged piece;
step S5: quenching the forge piece, wherein the quenching temperature range is 1017-1024 ℃, the temperature of the forge piece is kept for 3-7 h, and the forge piece is cooled to the room temperature;
step S6: tempering the forge piece, wherein the tempering temperature range is 683-707 ℃, the heat of the forge piece is preserved for 4-9 h, and the forge piece is cooled to room temperature;
step S7: and (4) roughly processing a forged piece, and performing UT flaw detection.
Further, in step S2, the forging ratio of the forging is 6.15.
Further, in step S3, the temperature range of the forge piece remelting and heat preservation is 1140-1160 ℃, and the heat preservation time is 1.5 h.
Further, in step S4, the forge piece is subjected to heat preservation for 3-4 hours at the temperature of 960-980 ℃.
Further, in step S4, the forge piece is subjected to heat preservation for 10-12 hours at the temperature of 760-770 ℃.
Further, in step S5, the quenching temperature is set to 1020 ℃, and the temperature of the forge piece is kept for 4-5 h.
Further, in step S5, the forging is cooled to room temperature by oil cooling.
Further, in the step S6, tempering and temperature setting are carried out at 690 ℃, and the temperature of the forge piece is kept for 6-8 h.
Further, in step S5, the forging is cooled to room temperature by oil cooling.
In conclusion, the invention has the following beneficial effects:
1. and controlling the last thermal deformation parameter of the forge piece and the control of the heat treatment system of the forge piece to crush coarse grain structures in all directions so as to obtain fine grains in all directions, wherein the grain size can still be maintained at the level meeting the sensitivity of 0.5mm after the performance heat treatment.
2. Through a special heat treatment process after forging, the inheritance of crystal grains is cut off, the crystal grains in all directions are further refined, the radial grain size is greatly improved, the purity of the forging is further improved, and the tensile property, the durability and the fatigue property of the forging are improved.
Drawings
FIG. 1 is a schematic diagram of the steps for improving the flaw detection quality of a X22CrMoV12-1 disk of a gas turbine.
Fig. 2 is a metallographic examination of example 1.
Fig. 3 is a metallographic examination of example 2.
Fig. 4 is a metallographic examination of example 3.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the following detailed description of the present invention is provided with reference to the accompanying drawings and the detailed description. The advantages and features of the present invention will become more apparent from the following description. It is to be noted that the drawings are in a very simplified form and are all used in a non-precise scale for the purpose of facilitating and distinctly aiding in the description of the embodiments of the present invention. To make the objects, features and advantages of the present invention comprehensible, reference is made to the accompanying drawings. It should be understood that the structures, ratios, sizes, and the like shown in the drawings and described in the specification are only used for matching with the disclosure of the specification, so as to be understood and read by those skilled in the art, and are not used to limit the implementation conditions of the present invention, so that the present invention has no technical significance, and any structural modification, ratio relationship change or size adjustment should still fall within the scope of the present invention without affecting the efficacy and the achievable purpose of the present invention.
Example 1:
a method for improving the flaw detection quality of an X22CrMoV12-1 disk of a gas turbine comprises the following steps:
step S1: preparing a forging raw material, wherein the raw material size is as follows: phi 400mm x 774 mm.
Step S2: and (3) carrying out forging improvement on the forge piece, wherein the forging improvement comprises upsetting and drawing out, the upsetting is carried out until H is 380mm (phi 570mm), the drawing out is carried out until phi 400mm multiplied by 774mm, the upsetting is carried out until H is 360mm, and the forging ratio is 6.15. Make the forging warp to the appearance of design through changing to forge on the one hand, on the other hand is through accurate control forging ratio, makes thick crystal structure breakage, avoids the condition that the forging ftractures appear in the degree of deformation simultaneously.
Step S3: and (3) returning the forge piece and preserving heat, wherein the returning temperature is 1140 ℃, the preserving time is 1.5h, and upsetting is carried out until the size is reached: phi 815 multiplied by 180, and controlling the deformation amount of a single fire number as follows: 50 percent. The coarse crystal structure is further broken, so that fine crystal grains can be obtained in all directions.
Step S4: performing heat treatment after forging, putting the forged piece into a furnace, heating to 960 ℃, preserving heat for 3h, cooling to 760 ℃ in the furnace, preserving heat for 10h, and finally, cooling to below 650 ℃ in the furnace and discharging. And cooling the forging to room temperature in an oil cooling mode.
Step S5: quenching the forgings, wherein the quenching temperature is 1017 ℃, the temperature of the forgings is kept for 4h, and the forgings are cooled to room temperature in an oil cooling mode.
Step S6: and (3) tempering the forging, wherein the tempering temperature is 685 ℃, the heat preservation time of the forging is 6h, and the forging is cooled to the room temperature in an oil cooling mode.
Step S7: and (4) roughly processing a forged piece, and performing UT flaw detection.
Step S8: physical and chemical detection: taking tangential mechanical properties, and carrying out room-drawing, high-drawing at 600 ℃, impact and FATT tests.
Example 2:
the procedure differs from example 1 in that:
step S3: the tempering temperature is 1150 ℃.
Step S4: and (3) performing heat treatment after forging, putting the forged piece into a furnace, heating to 971 ℃, preserving heat for 3.5 hours, cooling to 764 ℃, preserving heat for 11 hours, and finally cooling to below 650 ℃ in the furnace and discharging. And cooling the forging to room temperature in an oil cooling mode.
Step S5: quenching the forging, wherein the quenching temperature is 1020 ℃, the heat preservation time of the forging is 4h, and the forging is cooled to the room temperature in an oil cooling mode.
Step S6: and (3) tempering the forge piece, wherein the tempering temperature is 690 ℃, the heat preservation time of the forge piece is 7h, and the forge piece is cooled to the room temperature in an oil cooling mode.
Example 3:
the procedure differs from example 1 in that:
step S3: the tempering temperature is 1160 ℃.
Step S4: and (3) performing heat treatment after forging, putting the forged piece into a furnace, heating to 980 ℃, preserving heat for 4 hours, cooling to 770 ℃ in the furnace, preserving heat for 12 hours, and finally, cooling to below 650 ℃ in the furnace and discharging. And cooling the forging to room temperature in an oil cooling mode.
Step S5: quenching the forged piece, wherein the quenching temperature is 1022 ℃, keeping the temperature of the forged piece for 5h, and cooling the forged piece to room temperature in an oil cooling mode.
Step S6: and (3) tempering the forging, wherein the tempering temperature is 700 ℃, the heat preservation time of the forging is 8h, and the forging is cooled to the room temperature in an oil cooling mode.
And (3) ultrasonic flaw detection results of the forgings:
the forgings are selected from the three embodiments for ultrasonic flaw detection, the three samples can smoothly complete the flaw detection process according to the sensitivity of 0.5mm, and standard-exceeding defects are not found.
Test results of forgings FATT:
detection standard: meets the requirements: < 80 ℃.
Example 1: the FATT value was 40 ℃.
Example 2: the FATT value was 55 ℃.
Example 3: the FATT value was 52 ℃.
And (4) experimental conclusion: FATT (fracture area transformation temperature) is an important parameter for measuring the impact fracture performance of the forge piece, and the FATT of the forge piece is about 50 ℃, which indicates that the impact toughness performance of the forge piece at the standard 80 ℃ is ensured.
And (3) a forging metallographic detection result:
example 1: as shown in FIG. 2, the grain size was 6.5 grade, and the crystal structure was fine and uniform.
Example 2: as shown in FIG. 3, the grain size was grade 7, and the crystal structure was fine and uniform.
Example 3: as shown in FIG. 4, the grain size was grade 7, and the crystal structure was fine and uniform.
And (4) conclusion: the grain size of the forging is about 7 grades, which shows that the forging processed by the method can obtain fine grains in all directions, improve the purity of the microstructure of the forging, and react to a macroscopic level, thereby bringing better mechanical properties.
The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (9)
1. A method for improving the flaw detection quality of an X22CrMoV12-1 disk of a gas turbine is characterized by comprising the following steps:
step S1: preparing a forging raw material;
step S2: carrying out re-forging on the forge piece, wherein the re-forging comprises upsetting and drawing out;
step S3: the forge piece is returned to the furnace and is insulated, the forge piece is upset, and the deformation of the forge piece is controlled to be 50 percent;
step S4: performing heat treatment after forging, namely, putting a forged piece into a furnace, heating the forged piece to 960-980 ℃, preserving heat, then cooling the forged piece to 760-770 ℃, preserving heat, and finally, cooling the forged piece to below 650 ℃ in the furnace and discharging the forged piece;
step S5: quenching the forge piece, wherein the quenching temperature range is 1017-1024 ℃, the temperature of the forge piece is kept for 3-7 h, and the forge piece is cooled to the room temperature;
step S6: tempering the forge piece, wherein the tempering temperature range is 683-707 ℃, the heat of the forge piece is preserved for 4-9 h, and the forge piece is cooled to room temperature;
step S7: and (4) roughly processing a forged piece, and performing UT flaw detection.
2. The method for improving the flaw detection quality of the X22CrMoV12-1 disk of the gas turbine according to claim 1, wherein the method comprises the following steps: in step S2, the forging ratio of the forging is 6.15.
3. The method for improving the flaw detection quality of the X22CrMoV12-1 disk of the gas turbine according to claim 1, wherein the method comprises the following steps: in step S3, the temperature range of the forge piece remelting heat preservation is 1140-1160 ℃, and the heat preservation time is 1.5 h.
4. The method for improving the flaw detection quality of the X22CrMoV12-1 disk of the gas turbine according to claim 1, wherein the method comprises the following steps: in step S4, the forge piece is subjected to heat preservation for 3-4 hours at the temperature of 960-980 ℃.
5. The method for improving the flaw detection quality of the X22CrMoV12-1 disk of the gas turbine according to claim 1, wherein the method comprises the following steps: in step S4, the temperature of the forge piece is kept for 10-12 h at 760-770 ℃.
6. The method for improving the flaw detection quality of the X22CrMoV12-1 disk of the gas turbine according to claim 1, wherein the method comprises the following steps: in step S5, the quenching temperature is set to 1020 ℃, and the forging is kept warm for 4-5 h.
7. The method for improving the flaw detection quality of the X22CrMoV12-1 disk of the gas turbine according to claim 1, wherein the method comprises the following steps: in step S5, the forging is cooled to room temperature by oil cooling.
8. The method for improving the flaw detection quality of the X22CrMoV12-1 disk of the gas turbine according to claim 1, wherein the method comprises the following steps: in step S6, tempering and setting the temperature to 690 ℃, and keeping the temperature of the forge piece for 6-8 h.
9. The method for improving the flaw detection quality of the X22CrMoV12-1 disk of the gas turbine according to claim 1, wherein the method comprises the following steps: in step S5, the forging is cooled to room temperature by oil cooling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111550573.8A CN114277221A (en) | 2021-12-17 | 2021-12-17 | Method for improving flaw detection quality of X22CrMoV12-1 disk of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111550573.8A CN114277221A (en) | 2021-12-17 | 2021-12-17 | Method for improving flaw detection quality of X22CrMoV12-1 disk of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114277221A true CN114277221A (en) | 2022-04-05 |
Family
ID=80873046
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111550573.8A Pending CN114277221A (en) | 2021-12-17 | 2021-12-17 | Method for improving flaw detection quality of X22CrMoV12-1 disk of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114277221A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001073092A (en) * | 1999-09-06 | 2001-03-21 | Kobe Steel Ltd | 9-12% Cr HEAT RESISTING STEEL EXCELLENT IN HIGH TEMPERATURE STRENGTH AND TOUGHNESS, AND ITS MANUFACTURE |
| CN102586550A (en) * | 2012-02-29 | 2012-07-18 | 重庆宗学重工机械股份有限公司 | Heat treatment method for stainless steel heat-resistant steel forging |
| CN103602919A (en) * | 2010-12-28 | 2014-02-26 | 株式会社东芝 | Forging heat resistant steel, manufacturing method thereof, forged parts and manufacturing method thereof |
| JP2015193030A (en) * | 2014-03-31 | 2015-11-05 | 大同特殊鋼株式会社 | Forging method for disc-shaped article |
| CN106119479A (en) * | 2016-08-31 | 2016-11-16 | 无锡派克新材料科技股份有限公司 | A kind of method for annealing improving 13Cr9Mo2Co1NiVNbNB grain size |
| CN108031779A (en) * | 2017-11-29 | 2018-05-15 | 无锡透平叶片有限公司 | A kind of turbine blade and preparation method thereof |
| CN108220545A (en) * | 2017-12-07 | 2018-06-29 | 陕西宏远航空锻造有限责任公司 | A kind of heat treatment method of martensite thermostabilization stainless steel |
| CN108893684A (en) * | 2018-06-08 | 2018-11-27 | 中航卓越锻造（无锡）有限公司 | Low-intensity martensitic stain less steel ring forging and its forging method |
| CN110997960A (en) * | 2017-09-21 | 2020-04-10 | 三菱日立电力系统株式会社 | Gas turbine disk material and heat treatment method therefor |
-
2021
- 2021-12-17 CN CN202111550573.8A patent/CN114277221A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001073092A (en) * | 1999-09-06 | 2001-03-21 | Kobe Steel Ltd | 9-12% Cr HEAT RESISTING STEEL EXCELLENT IN HIGH TEMPERATURE STRENGTH AND TOUGHNESS, AND ITS MANUFACTURE |
| CN103602919A (en) * | 2010-12-28 | 2014-02-26 | 株式会社东芝 | Forging heat resistant steel, manufacturing method thereof, forged parts and manufacturing method thereof |
| CN102586550A (en) * | 2012-02-29 | 2012-07-18 | 重庆宗学重工机械股份有限公司 | Heat treatment method for stainless steel heat-resistant steel forging |
| JP2015193030A (en) * | 2014-03-31 | 2015-11-05 | 大同特殊鋼株式会社 | Forging method for disc-shaped article |
| CN106119479A (en) * | 2016-08-31 | 2016-11-16 | 无锡派克新材料科技股份有限公司 | A kind of method for annealing improving 13Cr9Mo2Co1NiVNbNB grain size |
| CN110997960A (en) * | 2017-09-21 | 2020-04-10 | 三菱日立电力系统株式会社 | Gas turbine disk material and heat treatment method therefor |
| CN108031779A (en) * | 2017-11-29 | 2018-05-15 | 无锡透平叶片有限公司 | A kind of turbine blade and preparation method thereof |
| CN108220545A (en) * | 2017-12-07 | 2018-06-29 | 陕西宏远航空锻造有限责任公司 | A kind of heat treatment method of martensite thermostabilization stainless steel |
| CN108893684A (en) * | 2018-06-08 | 2018-11-27 | 中航卓越锻造（无锡）有限公司 | Low-intensity martensitic stain less steel ring forging and its forging method |
Non-Patent Citations (3)
| Title |
|---|
| 米哈依洛夫: "《合金钢与非铁合金锻造工艺学》", 31 December 1992, 上海科学技术出版社, pages: 119 - 120 * |
| 米哈依洛夫: "《大型锻件材料及热处理》", 上海科学技术出版社, pages: 376 - 378 * |
| 锻件质量分析编写组: "《锻件质量分析》", 31 January 1983, 北京机械工业出版社, pages: 51 - 52 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101927312B (en) | Method for processing TC4 titanium alloy into forged rings | |
| CN101429637B (en) | Biphase titanium alloy thermal treatment method for acquiring two-state organization with raft-shape primary alpha phase | |
| Shi et al. | Effect of strain rate on hot deformation characteristics of GH690 superalloy | |
| CN114293102B (en) | Manufacturing method of 17CrNiMo6 forge piece | |
| Behrens et al. | Influence of process parameters on the hot stamping of carbon-martensitic chromium steel sheets | |
| AU2014358718A1 (en) | Nickel-based alloy, method and use | |
| CN109439861A (en) | A kind of heat treatment method of martensitic precipitation part | |
| CN114277221A (en) | Method for improving flaw detection quality of X22CrMoV12-1 disk of gas turbine | |
| CN108396125B (en) | A kind of processing technology of carburizing steel railway bearing forging crystal grain refinement | |
| Davey et al. | Fatigue Performance of the Novel Titanium Alloy Timetal 407 | |
| CN115449731B (en) | Preparation process of long needle-shaped basket structure of near alpha-type titanium alloy forging | |
| CN114182067B (en) | Forging and heat treatment method for martensite heat-resistant stainless steel special-shaped forge piece | |
| CN102560043A (en) | Heat treatment process for large 35CrMo steel axis forgings | |
| CN113523164B (en) | Forging and heat treatment process for high-strength forging of marine rudder system | |
| CN113201702B (en) | Thermal treatment method for eliminating deformation twin structure in R26 alloy based on thermodynamic simulation | |
| JPH11199995A (en) | Method for improving creep characteristic of titanium alloy and titanium alloy | |
| CN114472791A (en) | Manufacturing method of high-performance 30Cr2Ni4MoV wheel disc forging for gas turbine | |
| US3642595A (en) | Thermal grain refinement of maraging steel | |
| Dempster et al. | Structure and property comparison of Allvac® 718Plus™ alloy and Waspaloy forgings | |
| TW201925483A (en) | Fabrication method of free-cutting bi-phase Austempered ductile iron which is used to reduce the hardness of the ductile iron billet, increase the toughness, improve the cutting-work performance, and simultaneously improve the impact energy | |
| CN107529461A (en) | Remove GH901 high temperature alloy disk forge piece coarse-grains changes forging method | |
| Girdwood et al. | Recovery of creep properties of the nickel-base superalloy nimonic 105 | |
| John et al. | Age hardening treatment of Ti-6Al-4V alloy dome for aerospace application | |
| CN114293119B (en) | Heat treatment process method of combustion engine turbine blade made of Ni91 alloy | |
| JP2019010668A (en) | Method for manufacturing steam turbine material |
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 |